Rocket launch system and supporting apparatus

ABSTRACT

A rocket launch system includes a tubular rocket launcher carriage with electromotive cableway traction drives conveyed beneath a two axis pivot anchored to the earth, elevated into a co-axial transfer tube leading to three primary tether cables whose weight is offset by balloons. The carriage is conveyed to a docking station supported into the stratosphere by a pair of secondary cables suspended under an attachment frame for tensioning balloons. The carriage is engaged by a carriage end gripper guided by two sets of secondary cables and two sets of tertiary cables and lifted by a lower hoist guided by the secondary cables to a lift ring assembly. This lower hoist is supported by an upper hoist suspended from the tensioning balloons attachment frame. The carriage, which engages a lift ring guided by two secondary cables, is elevated further, rotated in azimuth and elevation, and rocket ejection occurs from a launch tube during freefall of the carriage, with engine ignition occurring at a safe distance. The carriages have traction drives which grip cables from which they derive power and rotate to drive the carriage from the low altitude to the high altitude. The traction drives rotate in the opposite direction as the carriage descends the cable following the launch of a rocket under gravitational force. The kinetic energy of the traction drive is converted to electrical energy which is fed back to the cables during descent of the carriage.

CROSS REFERENCE TO RELATED APPLICATION

This application claims the benefit of U.S. provisional patentapplication Ser. No. 61/337,645 filed Feb. 11, 2010, under Title 35,United States Code, Section 119(e), which is incorporated herein byreference in its entirety.

BACKGROUND OF THE INVENTION

Field of the Invention

The present invention relates to a system for delivering various typesof payloads to the upper atmosphere and beyond, and more particularly toa high cyclic rate launch rate rocket launcher with an upper launchstation. The cables' self weight is offset by lighter-than-air balloons.The cables are tensioned by one or more lighter-than-air balloons andanchored by a pivoting tether.

Description of the Prior Art

Many methods of delivering useful materials such as propellants, gasesfor life support, etc. and fabricated items to the upper atmosphere orbeyond, exist or have been proposed in recent publications.

These primarily involve rockets powered by chemical, nuclear or groundbased laser or maser energy sources. Various methods of reducing thecost per unit mass of delivering useful materials and fabricated itemsto the upper atmosphere or beyond, which involve rockets, exist or havebeen proposed.

These included re-usable rocket powered vehicles such as the soon to beretired United States of America's Space Shuttle, or Russia's nowinoperative Buran. Currently, only chemical multi-stage rockets orvehicles with strap on solid fuel powered rocket boosters, or rocketssuch as the USA's diminutive Pegasus, which is transported to highaltitude before launch, are known to be in service.

Proposed methods of decreasing the delivery cost to the upper atmosphereor beyond, most commonly involve transferring energy to the rockets byincreasing either their initial kinetic or potential energy beforeigniting the main motor or motors. Proposals by which this can beachieved include: elevation suspended under a disposable, free flight,lighter-than-air balloon or, forcible ejection at high velocity fromlarge guns utilizing either chemical propellants or compressed air orcompressed hydrogen or, transport to high altitude attached to airplanessuch as Virgin Galactic's White Knight Two or, transport to highaltitude towed on a cable tether behind an airplane or, acceleration tohigh velocity using ground based linear induction motors or, jet orrocket powered sleds, prior to igniting the rocket's main motor ormotors.

One proposed method for reducing the delivery cost, which does notinvolve rockets, is the so called “Space Elevator” where a large mass istethered to the earth by a single cable many thousands of miles long.The large mass orbits the earth in a geosynchronous orbit and keeps thecable taut. This cable would then be used in a manner analogous to arailway track on which a train travels.

The primary difficulty with this latter method is that the tensilestrength of the material required for the cable far exceeds any existingmaterial, especially since the self weight of the cable would beconsiderable. Another difficulty is to supply the vehicle climbing thiscable with sufficient energy to essentially climb out of the majority ofthe earth's gravitational field. A weightless, super strong, cablematerial would be ideal for such a “space elevator” but, this does notyet exist. Also, the problem of energy supply up thousands of miles ofcable has prompted the consideration of beamed microwave or laser powerto the climbing vehicle. The defocusing and obstructive effect of cloudsand the atmosphere on the beamed power is likely to greatly reduce theamount of power that actually reaches the climbing vehicle. Dissipationof energy on the return of the (climbing) vehicle to the earth is likelyto be quite wasteful because of the need for braking to prevent it fromexceeding the speed capacity of the mechanism holding the said vehicleto the cable.

Many of the current proposed methods require the development of newmaterials or massive structures and are unlikely to see commercialservice for many decades to come, if ever.

The majority of current launch methods involve the use of huge amountsof energy, derived primarily from fossil fuels such as coal or oil toproduce cryogenic liquid oxygen oxidizer, cryogenic liquid hydrogen orother liquid hydrocarbon fuels or solid propellants. This use ofnon-renewable resources is inherently inefficient because at each stageof production of the fuels there is a compounding of processinefficiencies. As well, the large mass and sometimes toxic nature ofexhaust material used to propel the vehicle out of the atmospherefrequently does ecological damage or may cause climatologicaldisturbances.

Accordingly, a need exists for a method of delivering useful materialssuch as propellants, gases for life support, etc. and fabricated itemsto the upper atmosphere or beyond, at a cost per unit mass delivered,far less than currently commercially available, which utilizes currentlyavailable materials and technologies. Furthermore, it would beecologically beneficial to minimize the mass of material used to propelthe vehicle out of the earth's atmosphere by the use of hydroelectric,geothermal or solar photovoltaic generated electricity to raise thevehicle as high as possible before igniting the vehicle's engine orengines.

Atmospheric monitoring has been in effect for over fifty years.Measurement of solar radiation, concentrations of trace gases,temperature, pressure and other parameters, by which the direction ofthe earth's climatological changes can be predicted, has greatlyincreased our understanding of our world's climate. It is of particularimportance with regards to the ozone hole, the continuous rise of carbondioxide and other “greenhouse” gases in the atmosphere, and now, themore than fifty chemical species in the earth's atmosphere.

As increased levels of “greenhouse” and ozone depleting gases occur,such as carbon dioxide, chlorofluorocarbons, nitrous oxide and sulfurhexafluoride, which cause global warming and other changes in the globalweather, there arises an increased requirement for atmosphericmonitoring on a more continuous basis. Current methods for monitoringatmospheric conditions involve heavily instrumented aircraft, manned andunmanned; free flight balloons with suspended instrument packages;rockets with sampling and instrument payloads; and ground based laserand radar stations.

These, with the exception of the ground based stations, cannot providemore than a relatively brief period of atmospheric data sampling. Thelongest duration of monitoring by non-ground based methods currentlydoes not exceed more than a few days in the case of balloons, and theshortest, such as rockets, might be measured in minutes. Many of thesemethods of atmospheric monitoring also utilize single use instrumentpackages, while existing ground based stations cannot obtain physicalsamples to determine the chemical composition, the bacterial/viralcontent, or the intensity and spectral analysis of sunlight and otherdata throughout the depth of the atmosphere.

Thus, there exists a need for constructions extending from the surfaceof the earth to a great height, on which instrumentation for continuousmonitoring and sampling of the atmosphere and, incident solar and otherradiation may be mounted.

Radio telecommunications and over the horizon radar are being moreextensively used for security reasons by many countries throughout theworld.

The recent worldwide security concerns about surprise terrorist attackshas driven countries such as the United States of America to increasethe level of surveillance by the use of radar and other means ofdetection utilizing various regions of the electromagnetic spectrum.This is evidenced by the 9/11 Commission Act of 2007 of Congress,relating in part to the interoperable radio telecommunication system forthe security of the United States. The range of ground based radar islimited by the curvature of the earth's surface and, in an attempt toachieve greater useful ranges, radar and other systems have been mountedon high flying aircraft or low altitude tethered balloons.

In a similar way, cellular radio telephony operators are currentlyseeking to enlarge the area serviced by the use of high altitudeaircraft, with receivers and transmitters, proposed to fly in closedcircuits over the service area. The extreme high altitude cases of thisare the INMARSAT and IRIDIUM satellite phone systems which utilizeextremely expensive and unrepairable geostationary satellites fortelecommunications.

Thus it may be seen that there is a need for lower cost, high altituderadar and radio telecommunications platforms.

The present invention also relates to tourism. The visitation of tallmonuments such as the Eiffel Tower, tall buildings such as the EmpireState Building, or high altitude natural features such as Mount Everestcontinues to be a common activity of tourists. Indeed, recently therehas also been increasing non-military interest in expensive highaltitude airplane flights. The recent “X Prize” for safe flight to 100kilometers or higher won by Burt Rutan's Space Ship One is furtherdriving the commercialization of high altitude transport. A problem withSpace Ship One and Space Ship Two is that their rocket motors uses aliquified nitrous oxide oxidiser and hydroxyl terminated polybutadienesolid fuel, which solid fuel produces an exhaust which includes soot,partially burnt rubber and other noxious materials. In recentpublications, it has been stated that alternative fuels for Space ShipTwo are being investigated, asphalt and paraffin. It is likely that,although these are cheap fossil fuels, combustion will not be complete.Yielding polluting exhaust products, in the case of asphalt, metaloxides and acidic sulphur compounds are likely. The effect of the sootalone, recently calculated for 1,000 launches per year by Martin Ross ofthe Aerospace Corporation, suggests stratospheric disruption and soaringtemperatures at the earth's poles. The launch rate published being onlya few times per week.

There is therefore a growing market for less expensive more frequenttransport of tourists to ever higher altitudes.

In the past few years, skydiving as a sport has changed to include ramair wing type parachutes, the use of auxiliary equipment such as smallrigid wings, miniature surfboards, rockets and even miniature turbojetengines. Further, the altitude from which skydivers have been jumpingfrom has been on the increase, although this has been limited by twomajor factors. These are the limited capability of civilian fixed wingairplanes and helicopters to operate at higher altitudes where thereexists a civil aviation half hour limit for oxygen enriched breathingsystems or, a requirement for a pressurized suit or cabin. In the shortterm, it is expected that civilian pressurized suits will becomeavailable to skydiving enthusiasts as the market for high altitudeskydiving develops.

Even more extreme forms of sky diving are even now being considered.These proposed forms involve jumping from the upper reaches of theatmosphere or even re-entry from space, as might occur when occupants ofdistressed orbital spacecraft are to be returned safely to earth.

Thus, there is an increasing market for novel, and higher altitudeplatforms for the various new forms of skydiving. Indeed, there is alsoa continuing demand for low cost platforms at altitudes of up to tenthousand feet.

In recent times, the rapid deployment of aircraft to sites of militaryinterest has become practically a necessity, for reconnaissance or otherpurposes. Additionally, there is a growing interest in commercialhypersonic transport. Towards this end, hypersonic aircraft withsupersonic combustion engines are being developed in many countries tofulfil these perceived needs.

However, the engines of such aircraft, designed to operate efficientlyat higher Mach numbers have been reported to require the attainment of avelocity in excess of three times the speed of sound for them to start.Considerable complexity, with a concomitant weight penalty is requiredfor an engine to operate in the various flight regimes from stationaryto hypersonic. Apart from using rocket boosters to achieving startingspeed, the other design path appears to require a two part engine. Thefirst part is a turbofan or turbojet engine which predominates in theflight regime from subsonic to low Mach number supersonic, transitioningto the supersonic combustion engine at high Mach numbers, and shuttingdown the first part.

Engines designed to operate in the hypersonic range only, many with nomoving parts, would therefore be lighter in weight, simpler inconstruction, and hence less expensive.

In 2003, the manned space shuttle Columbia of the United States ofAmerica was destroyed upon re-entry into the earth's atmosphere, due tostructural damage which occurred during the launch phase. As well, overtime, there has also been an accumulation of orbital craft in need ofrepair; and distressed orbital craft, and objectionable and dangerousdebris which needs to be removed from orbit.

Since craft such as the Columbia space shuttle of the United States areheavy, and they lack main engines that can operate for significantlengths of time after re-entry due to the hazards and weight penaltiesof carrying cryogenic or other fuels for use on the return flight inatmosphere, these craft must leave orbit at specific points if they areto be able to glide to the few airports with runways of sufficientstrength and length which exist close to its orbital track.

Thus, it is inevitable that others will create smaller craft capable ofperforming useful work outside the atmosphere, with the capability offlying under their own power in subsonic, supersonic or sustainedhypersonic flight in the earth's atmosphere. These are likely to belaunched using rocket power and, after re-entry at any point, fly to anyof the multitude of existing civilian or military airfields suitable forsuch smaller aircraft and, land safely.

These will be used for the quick, safe retrieval of passengers ofdamaged orbital craft and, repair or removal from orbit of distressedunmanned orbital craft, and objectionable and dangerous debris. Anothertype, soon to come into service, is a small service vehicle forrefueling or attaching to distressed space craft and acting as a tug toextend the useful life of such vehicles. Further small craft or rocketscan be used to launch small satellites, or modular components for theassembly and fuelling of large constructions in orbit which may be usedto escape the earth's gravitational field to possibly deflect dangerousasteroids, or explore the solar system. The European Space Agency andRussian equivalent Roscosmos have recently begun to consider thecreation of a shipyard in low earth obit to facilitate moon or marsmissions utilizing the yet to be built cargo return advanced re-entryvehicle (ARV).

Additionally, it is expected that there will be a continuing need toservice satellites and, other orbital craft. This servicing couldinclude delivering food, fuel, compressed or liquefied gases forbreathing or other uses, medical and scientific supplies, electrical,mechanical or other equipment to replace or upgrade spacecraft systems,transporting sick or injured personnel, or replacing personnel.

Thus, there is expected to be a need for a quick, inexpensive means oflaunching modular components for assembly and fuelling in space, smallutility craft, small satellites and other devices.

The sensitivity of many telescopes used in astronomy has been greatlydegraded due to atmospheric dust and aerosols as light is reflected orscattered by the aforementioned particles. The least affected telescopesare generally to be found at the top of remote mountains, above much ofthe atmosphere where most of the dust and aerosols are to be found.

Thus, there is a further need for high altitude platforms on whichsensitive telescopes may be mounted. Particularly, multiple platformsand telescopes may be used to simulate an extremely large aperturetelescope as currently used to locate planets in other solar systems.

As the Indonesian tsunami disaster unfolded in December 2004, it wasclear that reconnaissance of many of the affected areas and subsequentdelivery of initial relief supplies did not occur until days or evenweeks after the event, with the consequence that many tens of thousandsdied, more than if early relief had been available. Thus, there is aneed for a fast suborbital rocket launching system to deliver numeroussmall unmanned reconnaissance drones and thousands of tons of terminallyGPS guided parachute delivered relief supplies using simple GPS-guideddisposable rockets.

BRIEF SUMMARY OF THE INVENTION

Accordingly, a need exists for a method of delivering useful materialssuch as propellants, gases for life support, etc. and fabricated itemsto the upper atmosphere or beyond, at a cost per unit mass deliveredthat is far less than currently commercially available, which utilizescurrently available materials and technologies. Furthermore, it would beecologically beneficial to minimize the mass of material used to propelthe vehicle out of the earth's atmosphere by the use of hydroelectric,geothermal or solar photovoltaic generated electricity or otherrenewable source of energy to raise the vehicle as high as possiblebefore igniting the vehicle's engine or engines.

An object of the present invention is to provide a high launch raterocket launcher for sending payloads to space, as well as to satelliteslocated in space.

Still another object of the present invention is to provide a highlaunch rate rocket launcher which may utilize hydroelectricity or otherrenewable energy for elevating the rocket to launch altitude.

It is another object to utilize a more environmentally friendly fuel andoxidizer made using alternative or renewable energy.

Yet another object of the present invention is to provide an upperpivoting launch station utilizing electrically powered tubular launchcarriages, the launch station being connected to the ground by cables towhich are attached lighter-than-air balloons for tensioning andsupporting the cables and associated structures.

A further object of the present invention is to provide a means forrecovering potential energy involved in returning empty rocket launchingcarriages, after launch, to the earth, via tethers, through the use ofregenerative braking utilizing motor generators, for re-use.

Yet another object of the present invention is to provide atmosphericmonitoring on a more continuous basis as increased levels of“greenhouse” gases or other pollutants in the atmosphere cause changesin global weather.

A further object of the present invention is to provide high altituderadar and radio telecommunications platforms to greatly increase thespatial volume and area of earth's surface respectively covered.

Another object of the present invention is to provide continuous,reasonably priced commercial access for tourists to visit levels of theatmosphere inaccessible by other means except for rockets, aeroplanes orfree flying lighter-than-air aircrafts.

Still yet another object of the present invention is to provide higheraltitude platforms than are presently available for the various newforms extreme altitude or space skydiving, as well as low cost platformsat altitudes up to ten thousand feet which can be accessed withoutsupplementary oxygen or a pressure suit.

Another object of the present invention is to provide a quick,inexpensive means of launching small utility craft for safe retrieval ofpassengers of damaged orbital craft, repair, upgrade or removal fromorbit of distressed unmanned orbital craft and objectionable anddangerous debris.

Yet another object of the present invention is to provide high altitudeplatforms above the earth's cloud layers on which sensitive telescopesmay be mounted, especially those which can combine by computationalmeans, the electromagnetic waves inclusive of light and radio waves,received in such a manner as to act as a single telescope of a diameterequal to the distance of the outermost members of the array, forsuperior observations than are presently available, except from space.

A further object is to provide a means for servicing satellites andother orbital craft, for example for supplying food, compressed orliquefied gases for breathing or other uses, fuel, medicine andscientific supplies, electrical, mechanical or other equipment toreplace or upgrade spacecraft systems, and for transporting sick orinjured personnel, or replacing personnel.

It is an object to provide a transporting system for transportingrocket-loaded carriages along cables extending up through the atmosphereto a launch station.

It is a further object for providing carriages for carrying rocketsalong cables to a launch station located high in the atmosphere.

It is yet an additional object to provide an apparatus for holding anddirecting rocket-loaded carriages to the apparatus for conveying thecarriages along the cables to a launch station located high in theatmosphere, and for conveying empty carriages from the launch station tothe ground.

Yet a further object is to provide a system for safely storing rockets,and for delivering the rockets or rocket-loaded carriages to theapparatus for holding and directing the rockets or rocket-loadedcarriages to the apparatus for conveying the rockets or rocket loadedcarriages to a launch station located high in the atmosphere.

The provision of the apparatus for conveying rocket-loaded carriages isalso an object of the invention.

Another object of the invention is a system for conveying rockets,components of rockets, carriages for rockets and/or holders of conveyingdevices for rockets from a storage facility to a holding and assemblyfacility, for subsequent transport to the apparatus for raising therocket-loaded carriage to a launch station.

It is a further object of the present invention to provide a transverseloader for loading rockets into carriages.

An additional object is the provision of an elevating assembly forelevating a rocket-loaded carriage to the apparatus for loading therocket-loaded carriage into a set of elevated cables to a rocket launchstation.

It is an additional object to provide a turret for receiving arocket-loaded carriage, and related apparatus for orienting arocket-loaded carriage to a guide structure apparatus for disposing therocket-loaded carriage on the cables directed to the launching station.

It is still a further object of the invention for providing devices forconnecting lighter-than-air balloons to a cable system to stably holdand separate the cables which are directed to the launching station.

Another object of the invention is to provide a docking station fordocking a rocket-loaded carriage on a set of cables going to thelaunching station.

The object of providing electrical power for transporting arocket-loaded carriage along a cable system to the elevated launchingstation is another goal of the present invention.

Another object of the present invention is to provide a lift ring forlifting a rocket-loaded carriage along the cable system above thedocking station.

An additional object is the provision of a device for separating cablesfrom the ground to an elevated launching station, and for stabilizingthe cables.

It is also an object of the present invention to provide connectingapparatus for attaching frames and other apparatus to cables extendingbetween the ground and an elevated launching station.

The provision of an apparatus for holding a rocket within a carriage isalso an object of the present invention.

Another object is the provision of a telescope mount for use with a setof cables held upright in the atmosphere.

The provision of a rocket to be carried upwardly in a carriage forholding a person or persons, or equipment and supplies, is also anobject of the present invention.

An additional object of the present invention is an improved hydrostaticpressure compensating suit to be worn by a person to permit theendurance of high accelerations during rocket launch and atmosphericre-entry.

These objects are achieved according to the preferred embodiments of theinvention discussed below. Other objects will be apparent to thoseskilled in the art from the inventive concepts as discussed below andfrom the attached claims.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 depicts in schematic form some of the features of a preferredembodiment of the rocket launch system according to the invention.

FIGS. 1A and 1B are detailed views of the features shown in FIG. 1.

FIG. 2 is a schematic view showing the assembly and basic loadingportion of the rocket launcher system according to the preferredembodiment of the invention.

FIG. 3 shows the loading of a rocket into a lateral conveyance deviceaccording to an aspect of the preferred version of the invention.

FIG. 4 is a schematic view showing a different view of a carriageholding a rocket, a tipping mechanism and a lateral conveying device.

FIG. 5 is a schematic view of the plan layout showing a tracked loop forcarriages, storage racks, rocket holding and assembly stations,carriages, fuel storage apparatus and an electrical supply systemrelating to readying rockets for launching pursuant to the preferredembodiment of the invention.

FIG. 5A is an enlarged detail of a portion of tracks illustrated in FIG.5.

FIG. 6 shows in schematic form, the loading of a rocket into a fuellingor assembly bay according to a preferred embodiment of the invention.

FIG. 7 shows a detail of a transverse loader as shown in FIG. 6.

FIG. 7A is an enlarged detail perspective drawing of a leg and twistlock pin shown in FIG. 7.

FIG. 8 is a schematic view showing the operation of an elevatingassembly of the preferred embodiment of the invention with a lateralconveying device, and a rocket holding carriage.

FIG. 8A is an enlarged detail view of one version of apparatus forsupporting a turntable for rotation.

FIG. 8B is an enlarged detail view of another version of apparatus forsupporting turntable 72 for rotation.

FIG. 8C is a schematic view of the location of a rocket in a carriagelocated on a turntable, all according to a preferred embodiment of theinvention.

FIG. 9 is a schematic view of an elevating assembly, a rotating bed, alateral conveying device, a portion of a carriage according to apreferred embodiment of the invention.

FIG. 9A is an enlarged perspective view of a tapered, alignment pin.

FIG. 9B is an enlarged perspective view of a fractional twist lock pin.

FIG. 9C is an enlarged detail view of the base of a carriage.

FIG. 10 shows the apparatus for receiving, aligning and commencing theinsertion of a rocket holding carriage into the cableway according tothe preferred embodiment of the invention.

FIG. 10A is an enlarged detail view of a cable spacer.

FIG. 11 shows a further portion of the preferred part of the inventionwith respect to the cable system for transporting rocket holdingcarriages.

FIG. 12 is a detail of the upper portion of the preferred form of theinvention in schematic form showing a balloon assembly for elevating acable assembly and parts disposed thereon according to a preferredaspect of the present invention for lifting the rocket holding carriage.

FIG. 13 is a schematic view of an upper part of a preferred part of thepresent invention showing a portion of the cable assembly, and differentcomponents attached thereto.

FIG. 13A is an end view of a carriage with an end cover in the openposition.

FIG. 13B is a perspective view of an end of the carriage for use in theapparatus shown in FIG. 13, and FIG. 13C is a side, partlycross-sectional view of the carriage showing operating positions of someof its components.

FIG. 14 is a schematic cross-sectional view of the preferred embodimentof the invention showing a cable assembly and different parts attachedthereto.

FIG. 14A is an enlarged detail view of part of a carriage end gripper.

FIG. 15 is a schematic view of a preferred embodiment of the inventionshowing a stabilizing portion for the balloons and the cable assembly.

FIG. 15A is a detailed view of a portion of the stabilizing portion forthe balloons shown in FIG. 15.

FIG. 15B is an exploded perspective view of the connection of an upperspacer to a cable, and FIG. 15C is a plan view thereof.

FIG. 15D is an enlarged perspective view of cable attaching structurefor the middle of a spacing assembly arm.

FIG. 15E is an exploded perspective view of the connection of a lowerspacer to a cable and to a large harness.

FIG. 16 is a detailed schematic plan view of part of the stabilizingportion of the preferred form invention, taken in the direction 16-16 inFIG. 15.

FIG. 17 is another detailed view of part of the stabilizing part of thepreferred embodiment of the invention, taken in the direction 17-17 inFIG. 15, showing certain force vectors.

FIG. 18 is a perspective schematic view of a stabilizing assembly withthrusters according to the preferred embodiment of the invention.

FIG. 19 is a perspective view of a cable stabilizing device according toa preferred form of the invention.

FIGS. 20A and 20B are side views of two of many sets of lighter-than-airballoons attached to a cable assembly according to preferred forms ofthe invention.

FIG. 21 is a perspective view of a multistranded cable as may be used inthe cableway of the launch system, according to preferred form of theinvention.

FIG. 22 shows the construction for mounting items to the side of a cableas shown in FIG. 21.

FIGS. 23 and 24 are cross-sectional views of variations of theconstruction shown in FIG. 22.

FIG. 25 shows in cross-sectional view the engagement of a cable by thewheels of a traction drive for driving up or down said cable, accordingto a preferred form of the invention.

FIG. 26 is a perspective view of a retractable arm assembly, accordingto a preferred embodiment of the invention.

FIG. 27 is a detail showing a retractable arm assembly for holding arocket in a carriage according to the preferred embodiment of theinvention.

FIG. 28 is a schematic view of the upper portion of a preferredembodiment of the rocket launching invention if a telescope is to bemounted on top of the main lift balloon or balloons.

FIG. 28A is a perspective view of the upper portion of FIG. 28.

FIG. 28B is a detailed, enlarged detail cross-sectional side view of aportion of the apparatus shown in FIG. 28 including a geared rotationaldrive system and a ring bearing, and FIG. 28C is taken in the direction28C-28C in FIG. 28B, and showing generally how cables may be terminated.

FIG. 29 shows a possible telescope mount for use in the embodiment shownin FIG. 28, the view being in a detailed, perspective form.

FIG. 30 is a schematic view of a rocket for launching a single spacesuited person, according to a preferred embodiment of the invention.

FIG. 31 is a variant of the rocket for multiple, individually releasablepods or space suited persons.

FIG. 32 shows a space suited person on a detachable re-entry frameutilizing an aero-spike for shockwave initiation.

FIG. 33 shows another variant of a detachable re-entry frame utilizingan aero-spike for shockwave initiation.

FIG. 34 is a schematic of a space suit to be worn by an occupantaccording to a preferred embodiment of the invention for use in exitingand re-entering the atmosphere.

FIG. 34A is a detail of the space suit helmet shown in FIG. 34, and FIG.34B is a further detail of the space suit helmet of FIG. 34.

FIG. 35 shows an apparatus for one method of varying the internal volumeof a space suit shown in FIG. 34.

FIG. 36 is a detailed view of a person's limb within a portion of thespace suit of FIG. 34.

FIGS. 37 and 38 show re-entry capable aero space plane versions of therocket assemblies mounted on top of rockets, one with wings extended andone with wings folded for the transport within a carriage, according toa preferred embodiment of the invention.

FIG. 38A is a pictorial view of a lifting-body type aerospace plane withfolded lift and control structures for use with a preferred embodimentof the invention.

FIG. 39 is a schematic view of a satellite or other payload carried on arocket according to part of a preferred embodiment of the invention withjettisonable, aerodynamic, protective shells.

FIGS. 40 and 41 show a perspective and a cross-sectional view of a rodas a type of cable to be used instead of a wire rope.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS OF THE INVENTION

The preferred embodiment of the invention is initially described ingeneral terms referring to some components described in more detailbelow. The general components are shown in such general terms in FIGS.1, 1A and 1B. The preferred embodiment is a rocket launch system 1 whichincludes apparatus for moving a rocket 18 to be launched. Rocket 18 isfirst either in a container or rocket-transporting device such as acarriage 20 or is to be loaded into carriage 20, from storage racks 7.Carriages 20 have cylindrical lengthwise bores into open-ended,heat-and-pressure resistant continuous tubes 836 (FIGS. 13, 13C) whichare disposed and held in place for receiving a rocket 18. Carriages 20are weatherproof and have a longitudinal axis, which is the samelongitudinal axis of tube 836. Rockets 18, components thereof, andcarriages 20 which may or may not be loaded with rockets 18, areconveyed to storage racks 7 by an appropriate transport railing car on arailway 3 to an off loading area 5. A crane 48 carries respectivelyrockets 18, and/or carriage 20 and/or a component of rocket 18 travelsor is used to maintain various parts of the rocket launch system 1 onrelatively narrow crane tracks 78. Rockets 18 may have fins 21 (FIG. 7),and each carriage 20 has internal supports in addition to tube 836.

A transverse loader 50 travels on tracks 90 in the directions shown byarrows A in FIG. 1A, tracks 90 being located further apart from eachother than crane tracks 78. Transverse loader 50, which ispreferentially used to transfer rockets 18, carriages 20, etc., fromstorage racks 7 to assembly or fuelling bays 10, includes trucks 92 fortravelling on tracks 90, and has a wheeled truck 98 movable on a pair oftransverse, parallel rails 97 on top of beams 96, and an elevatorassembly 100 attached to a wheeled truck 98. Crane 48, which ispreferentially used to perform launch system maintenance, may also beused to remove rockets 18, and/or carriages 20, etc. from storage racks7, and transfer rockets 18 and/or carriages 20 to assembly/fuelling bays10 (there would usually be a plurality of assembly bays 10). Elevatorassembly 100 moves on rails 97 in the direction shown by the arrows B.Carriage 20, which may or may not have been loaded with a rocket 18 byone way or another, is placed in assembly bay 10. The entire operationis controlled by appropriate control equipment at a local launch controlor systems control bunker 120.

Referring to FIGS. 1A and 2, a lateral conveying device 46 carriescarriage 20 with rocket 18 loaded therein along a set of tracks 17disposed in below-the-ground paths 14 and 14A, which are located betweenvertical walls 16. Path 14A (also referring to FIG. 5) leads to a closedloop pathway 15 also having tracks 17. Lateral conveying devices 46 movein the direction shown by arrows C. Lateral conveying device 46transports carriage 20 with rocket 18 to a launcher 119 which includesan elevating assembly 60. Elevating assembly 60, referring to FIGS. 8and 9, includes an upper swiveling mechanism 61. Carriage 20 is elevatedto an above-the-ground turntable mechanism 63. Turntable mechanism 63includes a turntable base 122 and a turret assembly 123 (FIGS. 8, 10,11). Turret assembly 123 comprises a turntable 72, a lower guide tube124 and a secondary guide structure 125, the latter being operativelyconnected to a set of power and transporting primary cables 27.

Primary cables 27 are electric energy providers for rocket-loadedcarriages 20 being transported thereon. Electrical energy could beprovided by one set of electricity-conducting cables, and carriages 20could be transported by a second set of strong, transporting cables.However, the electric power lines and the rocket-transporting lines havebeen integrally combined into one of a set of power and transportingprimary cables which function both as an electrical energy carrier andto support rockets (preferably in carriages to transport said carriagesto and from high altitudes). Primary cables 27 have a low end portion ator near secondary guide structure 125 or turntable mechanism 63 and ahigh end portion which when in use is at high altitudes. Said power andtransporting primary cables 27 are preferably three in number forcarrying three-phase electrical power. Primary cables 27 referring toFIGS. 1, 1B, 11, 12, 13 and 14, are connected to a docking station 166,from which extend a set of secondary cables 184. Cables 184 operativelyguide a lift ring assembly 182, which is adjusted to an appropriateheight above docking station 166 once the pre-selected launch azimuthangle is adjusted with carriage 20 engaged by lift ring assembly 182 andan upper ring part 172 of docking station 166. After being lifted out ofengagement with upper ring part 172 and released from a carriage endgripper 196, lift ring assembly 182 is adjusted to the pre-selectedlaunch elevation angle. Lift ring assembly 182 is positioned abovedocking station 166 and located at significant altitudes for the finalstep in the launching of rockets 18 as explained below.

Cables 27, 184 and any other cables are supported to the upperatmosphere by a series of lighter-than-air balloons 164 and 160, theballoons are composed of a skin holding a lighter-than-air gas. Saidlighter-than-air balloons 164 are attached to said primary cables 27intermittently along the length of said primary cables 27 to supportcumulatively the self weight of said set of primary cables 27 and anystructure carried by said primary cables 27. Balloons 160 support theotherwise unsupported portion of cables 27, and any structures attachedthereto, and all structures and assemblies from and including dockingstation 166 up to said balloons 160, and tension cables 27 and 184 sothat they may carry a useful load. Cables 27 are separated from eachother by a set of spacer or stabilizer assemblies 158. (Cables have beenshown throughout most of the description as wire ropes, but they couldbe rods as explained later.)

Each assembled rocket 18 within a carriage 20 is transported from anassembly bay 10 into lower guide tube 124, then into secondary guidestructure 125, and thence to docking station 166 by means of a drivingstructure which can be a set of traction drives 26 and electricallypowered energizing apparatus 168. Traction drives 26 can comprise a setof traction drive wheels 26A connected to apparatus for convertingelectrical power to mechanical power and for interconnecting togetherthe mechanical and electrical apparatus. Thus, a set of gears in agearbox G can be operatively connected to electrically poweredenergizing apparatus 168. The latter can include a motor-generator M-Goperatively connected to gears in gearbox G as shown in FIGS. 9C, 15Cand 25. Traction drives 26 are built into carriage 20. Carriage 20travels along and electrically powered energizing apparatus 168 derivespower from primary cables 27 as when carriage 20 is lifted up (orclimbs) cables 27 and other cables connected to them as described belowby traction drives 26. The self weight of cables 27 and all itemspermanently affixed to said cables are periodically offset bylighter-than-air balloons 164 and which are held taut bylighter-than-air balloons 160. Traction drive wheels 26A andelectrically powered energizing apparatus 168 (composed of gears ingearbox G coupled to motor generator M-G) convert electrical energy tokinetic energy to energize electrically powered energizing apparatus168. The latter is advantageously a reversible electrically poweredenergizing apparatus for converting potential energy to electric poweras carriage 20 descends, and delivering electric power to the electricpower lines forming part of the cables upon which carriage 20 istraveling. When carriage 20 requires electrical energy to ascend, wheels26A are driven by motor generator M-G via converting apparatus such asset of gears in gearbox G which rotate in response to being energized bymotor-generator M-G. When carriage 20 descends under the influence ofgravity, traction drives 26 act as a regenerative brake and operategears in gearbox G (or any other device for changing rotational speed)which drives motor-generator M-G (or any other device for convertingmechanical energy to electrical energy). Balloons 160 and 164 preferablyhave inclined sides such as shown in FIGS. 1, 11, 20A and 28;cylindrical sides as shown in FIG. 20B, or can be spherical or haveother shapes as well. High altitude balloons are well known and arecontinuously being developed and improved. Appropriate balloons 160 and164 should preferably remain functional in the applications for thepresent invention for many months and optimally for years. Balloons forgoing to the stratosphere have been known and used since the 1950's.Carriage 20 is lifted further along secondary cables 184 and rotated andthen tilted according to predetermined amounts as discussed below, afterwhich rocket 18 is launched.

The foregoing description provides an overview of components of apreferred form of the invention. Set forth below is a more detaileddiscussion of the invention in its preferred forms.

Rockets 18 and their respective payloads are assembled, loaded intocarriages 20 and fuelled if required, and kept in blast-resistantassembly bays 10 prior to launch. Each bay 10 is located below theground surface and is constructed so as to limit damage in case there isan accidental detonation of the propellant of a rocket 18. Each bay 10has an inverted surface in the shape of an inverted frustum 12 referringto FIGS. 2 and 11 of a cone made of an appropriate reinforced concretematerial or the like for limiting the effects of any such blast bydeflecting it upwardly and laterally. Each bay 10 is connected by meansof below-the-ground paths 14 and 14A to closed loop path 15. Path 14ends at an inclined open chute 86 (FIG. 6) with upwardly sloping wall16A (FIG. 2) facing into the lateral opening of assembly bay 10. Thisdeflects any lateral component of the possible blast from bay 10 upwardsand away from the supporting apparatus (structures, equipment) forlaunch system 1, and from personnel. Path 14 then turns at approximately90 degrees to join with path 14A. Each bay 10 is capable of holding arocket 18 within a carriage 20. Each rocket 18 can comprise a shortduration booster rocket motor for ejecting rocket 18 from its open endedcontinuous tube 836 (FIG. 13A) within carriage 20 with such a velocitythat, even if the main rocket engine misfires, the short durationbooster rocket motor and rocket 18 will not fall and damage rocketlaunching system 1. The booster rocket motor would operate only withinthe heat and pressure resistant confines of the container in which it isheld, as described below. Each rocket 18 has one or more main motors fordriving rocket 18 to its design velocity.

Each carriage 20 has opposed end openings 24 (FIGS. 9C, 13, 13A), andhinged weather end covers or retractable membranes 30 (FIGS. 9C, 13,13A) at both ends thereof to protect rocket 18 in carriage 20 whilecarriage 20 travels from ground through the atmosphere. These covers 30can be swung to open both ends of carriage 20 or membranes 30 retractedto likewise open both ends of carriage 20, as shown in FIG. 13A. Alsowithin opposed end openings 24 are reversible variable pitch thrusters31 hinged parallel to one side of carriage 20 so that they may berotated to a position perpendicular to the ends by use of actuators 29(FIGS. 13B, 13C). Each carriage 20 has multiples of three tractiondrives 26 (FIG. 9C) equally spaced around the periphery of carriage 20for the purpose of gripping and pulling the carriage 20 up equallyspaced primary power cables 27. Cables 27 and 184 have suitably hightensile strengths and conductivity, as discussed below. Traction drives26 are powered by the foregoing three equally spaced primary powercables 27, cables 27 carrying three-phase power from which tractiondrives 26 draw their power. Traction drives 26 are reversible, usingelectrical power to raise carriage 20 or generate electrical power whenused as regenerative brakes. Traction drives 26 operating in theregenerative braking mode convert the potential energy of the carriage20 as it is lowered, into electricity which is fed back to cables 27,which recovered electricity may be used to assist the raising of otherloaded carriages in adjacent launch systems 1. Traction drives 386 (FIG.28) and 26 (FIG. 9C) operate in a similar manner. The interior ofcarriage 20 is designed to be capable of resisting the heat and blasteffects caused by the operation of the short duration booster rocketmotor. End covers or membranes 30 (shown in detail in FIGS. 9C and 13A)protect rocket 18 held in carriage 20 from any adverse weather and maybe used to contain inert or relatively inert gases within the interiorof carriage 20 surrounding rocket 18 such as nitrogen to inhibitcombustion of any reactive materials escaping from rocket 18 duringtransport to the high altitude launching position. The upper end ofcarriage 20 may have twist pin lock receptacles 32 (FIG. 13A) similar tofractional rotation twist pin sockets 154 (FIG. 9) (discussed below) toreceive twist lock pins 204 (FIGS. 12 and 13) similar to a fractionalrotation twist lock pin 144 (FIG. 9) (also discussed below) which areused to lift carriages 20 in preparing for a rocket launching process asdiscussed below.

Each carriage 20 has internal retractable arms 34 or 35 (FIG. 26, 27)which hold the rocket securely within carriage 20 such that centers ofgravity 36 and 37 (FIG. 13) of carriage 20 and rocket 18 respectivelyare stably positioned in the middle of carriage 20 at its center ofgravity. Small elastomeric or pneumatic wheels 372 (FIG. 27) may beattached to the periphery of the rocket to help prevent rubbing contactbetween the rocket and the inside of carriage 20 during ejection if therocket's thrust vector does not pass exactly through the rocket's centerof gravity. Retractable arms 35 and associated parts are discussedhereinafter.

Referring to FIGS. 3-6, there are different ways in which rockets 18could be loaded in carriages 20. In one version, a rocket 18 isinitially assembled horizontally, inserted into carriage 20, andinitially placed on a wheeled loader 38 (FIG. 3) in the direction shownby the arrow D. Carriage 20 is then placed in a hydraulic rotator 39,rotator 39 having a hydraulically or otherwise rotatable bed 40 mountedbetween stands 41 for rotation on pins 42 by means such as a hydraulicactuator 43 (or some other appropriate actuator). The piston rod ofhydraulic actuator 43 is almost entirely retracted inside the cylindersince carriage 20 has just passed over the piston and cylinder.Counterweights 44 are designed in each of the four corners of a bed 40,so as to cause the center of gravity of bed 40 to be co-incident withthe axis of rotation of pins 42 and with the center of gravity of therocket 18 and carriage 20 assembly—thereby reducing the actuation forcewhich the hydraulic actuator 43 or other means of rotation, has toexert. Rockets 18 could have previously been placed in horizontallyoriented carriages 20 of lateral conveying devices 46 (or similartransporters) prior to rotation to a vertical orientation by hydraulicrotators 39; or rockets 18 could have been placed in upstandingcarriages 20 previously situated on lateral carrying devices 46 inassembly bays 10 by means of transverse loader 50. Referring to FIG. 6,transverse loader 50 or crane 48 can be used to transfer empty carriages20 onto prepositioned lateral conveying devices 46 as explained below,in assembly bays 10, after which loader 50 or crane 48 would load arocket 18 into carriage 20.

Lateral carrying devices 46 are shown in FIGS. 1-6, 8, 9 and 10. Lateralcarrying devices 46 travel along paths 14, 14A and pathway 15 on tracks17. Pathway 15 forms a closed loop which passes under above-the-groundturntable mechanism 63 (FIGS. 1A, 8, 10, 11 discussed below) and carrycarriages 20 each loaded with a rocket 18 from blast resistant assemblybays 10 to elevating assembly 60 as shown in FIGS. 2 and 8, and carryempty carriages 20 as well. Each lateral conveying device 46 has aplatform 54 (FIG. 9) with a generally triangular recess 56 (FIG. 2, 4)for receiving the end of a carriage 20 so that carriage 20 is in anupright position, with the outer edges of carriage 20 fitting intorecess 56. Lateral carrying device 46 is shown having independentlysteerable wheels 58 (FIG. 9) for moving lateral conveying device 46 ontracks 17, and further has an appropriate steering mechanism to enablelateral conveying device 46 to travel along paths 14 and 14A, andpathway 15. An appropriate locking mechanism, which may include taperedalignment pins 142 (FIG. 9, discussed below), and fractional rotationtwist lock pins 144 (FIG. 9, discussed below), is provided for lockingcarriage 20 in recess 56 on platform 54. Lateral conveying devices 46further have similar receptacles as found on the bottom of carriages 20to receive alignment pins and fractional rotation twist lock pins 144,as explained below, for releasably securing devices 46 to upperswivelling mechanism 61 which as stated earlier is part of an elevatingassembly 60 as described later.

Along a portion of pathway 15, a series of rockets 18 and variantsthereof, and other items such as lateral conveying devices 46, carriages20 and variants such as pressurized tourist carriages and launchingsystem servicing carriages, are stored on storage racks 7 which aredivided by walls 64. Rockets 18, if they do not use solid fuel, can befuelled during storage on racks 7 or preferably in assembly bays 10using various combinations of propellant such as liquid-liquid orliquid-solid fuels depending on the type of rockets 18. One highspecific impulse propellant combination is liquid oxygen (LOX) andliquid hydrogen (LH₂) which can be stored in storage tanks 65 and 66respectively, as shown in FIG. 5.

This fuel combination can be produced in a most environmentally friendlymanner, by using a system wherein one or more hydro-turbines delivermechanical power and possibly other hydro-turbines drive electricalgenerators 62 which are included in a power facility 468. Thehydro-turbine(s) receive water from an appropriate source, such as ariver with sufficient pressure and mass flow rate, to power anelectrical substation 70 from coupled electrical generators 62, anddirectly drive compressors as found in gas liquefaction plants such as awater electrolysis and gas liquefaction sub-plant in plant 74.Electrical power from substation 70 can be used to operate waterelectrolysis sub-plant in plant 74, and may be used to provide auxiliarypower to a hydro-turbine driven gas liquefaction sub-plant in plant 74for liquefying the resultant oxygen (O₂) and hydrogen (H₂), which arerespectively stored in LOX storage tank 65 and LH₂ storage tank 66, aswell, the electrical power being used to supply energy to all otherparts of launch system 1 and its supporting apparatus requiring suchpower. Other sources of energy such as nuclear fission may be used as analternative if hydroelectric and hydro-turbine derived shaft horse powerare not available. Renewable sources of energy such as geothermal,hydropower or solar are preferred.

As explained earlier, rockets 18 are transported on the ground whilebeing contained in carriages 20. Lateral conveying devices 46 can movealong paths 14 and 14A, and pathway 15 on relatively narrow, parallelrails 17 (compared to tracks 90 discussed hereinafter). An emptycarriage 20 on storage rack 7 is shown in FIGS. 5 and 6 next to an emptylateral conveying device 46. Also shown in FIG. 5 is a pressurizedtourist carriage variant, service carriage vehicle variant, spareballoon containing carriages or a space tourism aerospace plane 76.Tracks 78 and a pair of tracks 90 (discussed below) (FIGS. 5 and 6),running parallel to the straight opposing parts of path 15, are used forthe movement of crane 48 and wheeled transverse loader 50. Emptycarriages 20 are shown on top of lateral conveying devices 46 movingalong pathway 15, from which they can be removed for refurbishing orreloading.

The loading system is shown in further detail in FIG. 6. Storage racks 7each hold either complete rockets 18 and/or component parts of rocket18, shown as rocket parts 18A, 18B, and 18C, and/or a space tourismaerospace plane 76 (FIG. 5), and/or empty carriages 20 or spare lateralconveying devices 46. Rocket parts 18A-18C could be combined for a finalrocket 18, but the invention is not so restricted. Rockets 18 with therespective rocket parts 18A-18C are fed to their respective places bymeans of railway 3 (see FIG. 1), which rockets 18, rocket parts, etc.could come from distant manufacturing facilities worldwide. Carriage 20and a lateral carrying device 46 are also shown in racks 7. Crane 48 cantravel on tracks 78 to assemble rocket parts 18A-18C in a bay within thestorage racks 7 and then into one of carriages 20. Crane 48 may also beused to service paths 14 and 14A, and pathway 15. Crane 48 has a cable49. Crane 48, using its cable 49 with appropriate lifting gear, may liftassembled rocket 18 and carry it into bay 10 (left part of FIG. 6) forinsertion into a preplaced carriage 20 atop lateral conveying device 46.A crane 48 is needed in addition to the other service equipment notedabove, for servicing the tracks 17, 78 and 90 and rails 97 (discussedhereinafter). Care must be taken in using crane 48 for transferringrockets 18, since crane's cable 49 may tend to sway during transfer andthe rocket suspended from cable 49 could be damaged.

As explained below, there is always a risk of accidental detonation of arocket 18 in bay 10 if highly reactive fuel-oxidizer combinations areused. In order to protect the various structures, equipment andpersonnel from the blast effects of such a detonation, a pair ofparallel, inverted L-shaped guide members 80 (FIG. 6) extend overopposite edges of bay 10. Each pair of guide members 80 has a blastcover 82 slidable in the direction shown by arrows E, and blast cover 82is slid under overlapping flanges 84 of guide members 80 prior tofueling. Blast cover 82, once located under flanges 84, cannot be movedeven if a blast occurs. Blast covers 82 are made of such a material asnot to be destroyed even if it has to withstand a blast within bay 10during assembly, fuelling or otherwise, the blast being directed awayfrom critical components via chute 86.

Transverse loader 50, shown in FIGS. 1 and 6, is part of a rocketloading system 88 including the pair of wide tracks 90 (wider thantracks 78 for crane 48) upon which ride the pair of wheeled trucks 92. Aguide assembly 94 comprising beams 96 and wheeled trucks 92 extendsacross wide tracks 90 and ride on trucks 92 which move on wide tracks90. Guide assembly 94 has parallel rails 97 as shown in FIG. 7 on top ofbeams 96 across which travels elevator assembly 100. The entiretransverse loader assembly 50 atop rails 90 is similar to a top runningdouble girder crane with end trucks. Parallel guide beams 96 are affixedto trucks 92. Wheeled truck 98 moves across parallel rails 97 as shownin FIGS. 1, 1A, 6 and 7. Transfer loader 50 includes elevator assembly100 as shown in FIG. 7 with a guide support apparatus 101 and anelevator 102 movable upwardly and downwardly as shown by the arrow F insupport apparatus 101 using appropriate electro-mechanical means,preferably counterweighted. Transfer loader 50 removes rockets 18, orempty carriages 20 or variants thereof, or carriages 20 holding varioustypes of rockets 18 or various components, from storage racks 7, toassembly bays 10, from which lateral carrying devices 46 transport thefueled rockets 18 within carriages 20 or other carriage variants tolauncher 119.

Referring further to FIG. 7, one embodiment of the details of the upperportion of transverse loader 50 in slightly modified form is shown. Asnoted above, transverse loader 50 has elevator assembly 100, with guidesupport apparatus 101 in which is deposed elevator 102. Supportapparatus 101 is shown having opposing extensions 103 which permits theconnection of apparatus 101 to wheeled truck 98 for moving elevatorassembly 100 across rails 97 on top of beams 96. In order to engage arocket 18 for lifting, elevator assembly 100 has depending legs 105 ofwhich a minimum of three is preferred for stability, which are connectedto a body 106 affixed to the lower end of elevator 102 permitting agrasping assembly 104 to be lowered into assembly bay 10, as indicatedby arrow G. Legs 105 are movable radially in guides 110 (as shown byarrows H in FIG. 7A) with respect to a rocket 18 located between legs105 so as to accommodate different diameter rockets. A fractionalrotation twist lock pin 111 or other means of attachment to rocket 18,is located at the free end of each leg 105, and the upper portion ofrocket 18 has equally spaced fractional rotation twist lock pin sockets109 or other receptacles for other means of attachment, for receivingthe respective twist lock pins 111 for enabling the secure attachment ofrocket 18 to elevator assembly 100. Pin sockets 109 are disposed in anose portion 19 of rocket 18, are generally parallel to the longitudinalaxis of rocket 18. Pin sockets 109 may have access covers 113 attachedto nose 19 of rocket 18, but being removable from the respective sockets109 as required to provide access to socket 109, while providing asmooth surface to rocket 18 when pin sockets 109 are not in use toreduce aerodynamic drag when the rocket is in flight.

Upper and lower stabilizing arm assemblies 114 may be provided forstabilizing a rocket 18 during lateral travel, held on elevator assembly100 while travelling along tracks 90 and rails 97. Stabilizing armassemblies 114 each have a hydraulic or other actuator 115 to which isattached an arm 116 of each arm assembly 114. Arms 116 are rotatablealong paths indicated by arrows I. A lug 117 is provided at the free endof each arm 116 for engaging an appropriately configured recess 118 inrocket 18 for receiving each of lugs 117.

As discussed previously, FIG. 6 shows a lateral carrying device 46loaded with a carriage 20 holding a rocket 18 moving in pathway 15towards launcher 119 discussed below. Another lateral carrying device 46carrying an empty carriage 20 is traveling away from launcher 119 whichdispensed a rocket 18 from carriage 20 at high altitude, moving inpathway 15 returning to an unoccupied assembly bay 10 to be reloadedwith rocket 18 or returning to storage rack 7 for servicing if required.

Referring back to FIG. 5, rocket launch system 1 further includeslauncher 119. A local launch control bunker 120 directs the operation ofrocket launch system 1, directing the flows of electrical energy to andfrom adjacent launch systems 1 from energy sources such as powerfacility 468 or other adjacent rocket launch systems 1, and housing thecomputer control and surveillance systems, utilizing data from thevarious measuring and imaging devices placed throughout launch system 1.This is where the personnel are generally located for controlling thelocal rocket launch system 1 and coordinating launches from the othermembers of the group of launch systems for minimizing the use of energy.

Elevating assembly 60 is disposed beneath the ground as shown in FIGS.2, 8 and 9. Elevating assembly 60 may have an elevating mechanism suchas a hydraulic piston rod 68 upon which sits upper swivelling assembly61 (FIG. 9) for rotating, by means of a rotary drive 134, a carriage 20with rocket 18 within, loaded on lateral conveying device 46 in thedirection shown by arrow J. Elevating system 60 described in more detailbelow with respect to FIG. 8, includes rod 68 having a wide,non-rotating lower bed 135 fixed to rod 68, mounted for supporting upperswivelling assembly 61. Upper swivelling assembly 61 is composed of arotatable bed 136 (with a table portion 141) mounted on top ofnon-rotating lower bed 135 (which is not part of turntable mechanism63).

Reference is now made to FIGS. 8 and 9. Piston rod 68 is part of apiston 67 extending from a hydraulic cylinder 69. Hydraulic cylinder 69,piston 67 and rod 68 do not rotate.

The foregoing hydraulic system is not the only way to operate theelevating mechanism. An electro-mechanical system could form theelevating mechanism.

Turning next to FIG. 10, turntable mechanism 63 is an above groundportion of rocket launcher 119 for receiving rocket-loaded carriages 20from elevating assembly 60 and orienting them to be transported isshown. The upward movement of rocket-loaded carriage 20 is shown by thearrow L. As stated above, turntable mechanism 63 includes turntable base122 and turret assembly 123. Turntable base 122 is attached to theearth.

Turntable 72 could be quite heavy, weighing several tons, and should besupported by a structure able to support such a heavy load, to withstanduplift and lateral forces, and rotate smoothly. A detail of anappropriate turntable support device is shown in FIG. 8A.

FIG. 8A shows turntable base 122 having a horizontal surface of a wheelengaging base 270 for being engaged by wheels 284, an upstanding tubularpart 272, and a horizontal, annular flange 274 extending outwardlytowards the outer circumference of turntable base 122. Turntable 72 hasa downwardly extending tubular part 276 at the perimeter of turntable72, from which extends an inwardly extending horizontal, annular flange278 having a number of wheel axle holders 280, 281 and 282 extendingtowards wheel engaging base 270, upstanding tubular part 272 andhorizontal, annular flange 274, respectively. Each axle holder 280, 281and 282 respectively holds the axles of wheels 284, 286 and 288respectively. Wheels 284, 286 and 288 ride on the surfaces of wheelengaging base 270, upstanding tubular part 272 and horizontal, annularflange 274 to enable the smooth circular rotation of turntable 72 shownin FIG. 8 by the arrow K. Alternatively, referring to FIG. 8B, turntablebase 122 could have a horizontal bearing base 290, an upstanding tubularpart 291 and a horizontal, annular flange 292. Likewise, turntable 72could alternatively have a downwardly extending tubular part 293 and aninwardly extending horizontal, annular flange 294. A set of rollingbearings such as bearing balls or crossed rollers 295 is located betweenhorizontal, annular flange 294 and each of bearing base 290 andhorizontal, annular flange 292, and appropriate annular bearing surfacessuch as grooves 296 would be used to enable the rotation of turntable 72with reduced friction than if bearings were not provided.

Turntable 72, based on the size of carriage 20, could be about 46 feetin diameter. For example, if the tubular interior of carriage 20 forcontaining rocket 18 has a radius of 8 feet, and the minimum thicknessof carriage 20 holding rocket is 2 feet, with a clearance of centrallylocated carriage 20 is 3 feet, the diameter of turntable 72 would beabout 46 feet. This is shown in FIG. 8C.

For a modest diameter of the tubular interior of carriage 20 forcontaining rocket 18 of 16 feet, carriage interior diameter, plus amodest (Δ=2 feet) clearance for the structure of carriage 20, andallowance of 3 feet (δ=3 feet) for the mechanism to permit turntable 72to rotate, the diameter of turntable 72 is about 46 feet and a flat side22 of carriage 20 is about 34.6 feet.

Turret assembly 123 is located at ground level, above bed 136 (FIG. 8),and is supported and restrained by turntable base 122. The vertical axisof rotation of turret assembly 123 coincides with the axis of elevatingassembly 60. Lower guide tube 124 has an orifice 71 for receivingrocket-loaded carriage 20 from lateral carrying device 46 through anorifice 73 as shown in FIG. 10 extending through turntable 72 andturntable base 122, by means of elevating assembly 60. Rotatable bed 136(FIGS. 8, 9) has tapered alignment pins 142 and fractional twist lockpins 144 to releasably lock lateral conveying device 46 with carriage 20thereon to bed 136. Carriage 20 is releasably locked in a similar mannerto lateral conveying device 46 using alignment pins 142 and fractionaltwist locking pins 144. Being so releasably locked, carriage 20 may bedriven as explained further below.

Still referring to FIGS. 8 and 10, turret assembly 123 further includesturntable 72 rotatable with respect to turntable base 122 in thedirection shown by arrow K noted earlier, a yoke 126 having a pair ofparallel, spaced apart, arms 127 which are pivotable above turntable 72.Between said arms 127 is disposed lower guide tube 124 (also part ofturret assembly 123). A pair of horizontal coaxial pivot pins 128extends through each of arms 127 and into opposing walls of lower guidetube 124, and is disposed through a pair of support members 129.Internal carriage guides 133 extend along the internal cylindrical wallsof lower guide tube 124 and are separated from each other by 120° forentering a set of corner recesses 130 (FIG. 9) extending in alongitudinal direction along the corner edges of carriages 20. Thecorner recesses contain traction drives 26. Lower guide tube 124 andsecondary guide structure 125 pivot in the rotational path shown by thearrow M in FIG. 8 by means of an appropriate rotational drive system,about the same horizontal axis defined by pins 128. Each of arms 127includes a counterweight 131 discussed below. The center point of lowerguide tube 124 is disposed vertically above turntable 72 of turretassembly 123 so that the axes of rotation of each of turntable and lowerguide tube 124 intersect orthogonally. The vertical axis of rotation ofturntable 72 being coincident with the axis of elevating assembly 60 andany lateral conveying device 46 and carriage 20 situated thereon.

Secondary guide structure 125 has an integral tube 143 which is held ata fixed distance from the common pivot of itself and lower guide tube124. Thus, secondary guide structure 125 is counterbalanced about itshorizontal pivot and has internal carriage guides 138 within theintegral tube. The lower end of integral tube 143 of secondary guidestructure 125 is capable of coming in alignment with the upper end oflower guide tube 124 so the tubes are coaxial, and internal carriageguides 133 and 138 are also aligned. Lower guide tube 124 is rotatableabout coaxial pivot pins 128, and rotates until its outer surfacesengage a stop 132 (FIG. 10) extending from an integral tube 330 so thatcarriage guides 133 and 138 are in alignment. Carriage guides 133 and138 are powered in the same manner as are power cables 27 (as discussedbelow) so that traction drives 26 in carriage 20 can utilize the power.The upper end of the tube of secondary guide structure 125 has internaltransitional attachment points for primary cables 27 to permit carriage20 to move from internal carriage guides 138 onto primary cables 27.

As shown in FIG. 2, lateral conveying devices 46, each loaded with acarriage 20 holding a rocket 18 moves along pathway 15 from assemblybays 10. Carriage 20 with rocket 18 is removed from pathway 15,transferred to rocket launcher 119, and after the rocket is launched theempty carriage 20 is returned to the empty lateral carrying device 46before proceeding along pathway 15, returning to assembly bays 10 orstorage racks 7.

Turning to FIGS. 8-10, elevating assembly 60 raises or lowers carriage20 with lateral conveying device 46 secured to rotatable bed 136, byraising piston 67 and rod 68 in the direction shown by arrow N (showingthe raising and lowering directions) to move carriage 20 into lowerguide tube 124, and clear of turntable 72. Rotatable bed 136 hasstructure described below for releasable attachment to lateral conveyingdevice 46 to accurately align traction drives 26 of carriage 20 withappropriate internal carriage guides 133 of lower guide tube 124.

Elevating assembly 60, lateral carrying device 46 and carriage 20 areshown in more detail in FIGS. 8 and 9. Hydraulic piston 67 has on itsupper end upper swivelling assembly 61 composed of non-rotating lowerbed 135, rotatable upper bed 136 and table portion 141. Lateralconveying devices 46 can travel to a location centered over elevatingassembly 60. As mentioned earlier, tracks 17 are likely to be ofnecessity wider than conventional railroad tracks. Upwardly taperedalignment pins 142 (four are shown) (shown in detail in FIG. 9A) extendfrom table portion 141 as do fractional twist lock pins 144 (four areshown) (shown in detail in FIG. 9B). These interconnect with lateralconveying device 46 as explained below. Of course, the location of therespective pins 142 and 144, and the respective sockets could bereversed between the lateral conveying devices 46 and the portion 141.

Upper swivelling assembly 61 of elevating assembly 60 is mounted on rod68 and can be raised as shown by arrow N to permit engagement of lowertapered alignment pins 142 and fractional rotation twist lock pins 144shown in FIG. 9 into corresponding alignment pin sockets 152 and twistpin socket 154 in lateral conveying device 46.

The upper surface of lateral conveying device 46 has upwardly extendingtapered alignment pins and fractional rotation pins which are virtuallythe same as lower tapered alignment pins 142 and fractional rotationtwist lock pins 144 extending from the top of table portion 141. Acorresponding alignment pin socket 155 and a twist lock socket 153 areprovided in the lower face of carriage 20 to receive the taperedalignment pins and fractional rotation pins on the top of device 46 toreleasably attach carriage 20 to lateral conveying device 46.

Lateral conveying device 46 has four wheels 58 positioned and contouredto ride on electric rails or tracks 17, and including tracks 17 adjacentto table portion 141, and are independently alignable as mentionedearlier. Lateral conveying device 46 may be powered from electric rails17 in ways similar to electric trains or tram cars (which would have tobe connected to an electric power source) or from some other on boardpower source such as fuel cells or internal combustion engines.

Lower guide tube 124 has internal carriage guides 133 (FIGS. 8, 10)which extend into each of corner recesses 130 extending along thevertical intersections of sides 22, also shown in enlarged form, (FIG.10) of carriage 20 to engage traction drives 26 of each carriage 20 tomove each carriage 20 along carriage guides 133, and to maintain theorientation of carriage 20 in lower guide tube 124. Carriage tractiondrives 26 are provided for gripping primary power cables 27. Carriagetraction drives 26 are mechanisms having cross sections partiallyenveloping primary cables 27 on which carriages 20 ride, and from whichthey derive power or to which they deliver power. Referring to FIG. 15C,one of traction drives 26 is shown as having two opposing traction drivewheels 26A in engagement with primary cable 27. Each traction drive 26includes a gearbox G and motor-generator M-G. As mentioned earlier,traction drives 26 may include motor-generators M-G and gearboxes G andopposing cylindrical wheels 26A operatively connected thereto, eachhaving an annular groove 137 for receiving a cable 27 as shown in FIGS.9C, 15C and 25. Wheels 26A rotate in opposite directions as shown byarrows O₁ and O₂. Traction drives 26 are positioned along the length ofa carriage 20. Surface roughening or modification could be provided onthe gripping surfaces of traction wheels 26A to enhance the appropriatesurface friction of the pairs of traction drive wheels 26A which ineffect pinch respective cables 27. Electric motor-generators M-G oftraction drives 26 derive electrical power from primary cables 27 (andany subsequent cables), to drive/rotate respective pairs of wheels 26Athrough gearboxes G as carriages 20 ascend primary cables 27, andmotor-generators M-G provide electrical power to primary cables 27 ascarriages 20 descend primary cables 27. The motors could rotate morethan one pair of traction drive wheels 26A. There also could beindividual motors operatively connected to individual pairs of tractiondrive wheels 26A. Much of this depends on the load being carried and thesize of carriage 20.

Traction drives 26 propel carriage 20 along cables 27 or guides 133 and138 (FIG. 10). Traction drives 26 generate power which is returned tothe cables when each carriage 20 is propelled in a reverse direction bygravitational force. The generation of this power causes a reaction tothe gravitational force and retards the motion of empty carriage 20 asit moves in a downward direction as occurs some time after launch ofrocket 18. Each traction drive 26 can have a minimum of one opposingpair of wheels 26A, as shown in FIG. 25. The traction drive motorsshould be of a constant torque motor or of a variable frequency drivetype to compensate for cable stretch or wheel slip, to cause each groupof wheels to contribute equally and maintain the carriage co-axial withthe centroid of cables 27 or internal carriage guides 133 of lower guidetube 124 or internal carriage guides 138 of integral tube 330 ofsecondary guide structure 125 when driving carriage 20 upwards.

As noted earlier, rocket launcher 119 according to the present inventionhas an elevating assembly 60 for raising or lowering a carriage 20vertically into or out of engagement with lower guide tube 124 mountedon turntable 72 of turntable mechanism 63. Lateral conveying device 46is movable with respect to table portion 141 so that fractionalrotational twist lock pins 144 can be received in twist pin sockets 154in the bottom of lateral conveying device 46. Elevating assembly 60elevates table 141 a short distance out of the bed of tracks 17 toengage the bottom of lateral conveying device 46. Table 141 is thenlocked onto the bottom of lateral conveying device 46 before its wheels58 and all of the table portion 141 are lifted above tracks 17 whereupontable portion 141 may be rotated with lateral carrying device 46 andcarriage 20 mounted thereon by means of rotating drive 134 to aligncarriage traction drives 26 with internal carriage guides 133 in lowerguide tube 124 which rotates freely or, if necessary with power assist,with turret assembly 123 to maintain alignment with the changing winds.This assures the necessary stable alignment of carriage 20 with rocket18 held therein, in lower guide tube 124.

Referring to FIGS. 1, 10 and 11, rocket launch system 1 includes aprimary set of cables 27 which are separated from each other by spaceror stabilizer assemblies 158. Spacer assemblies 158 are shown in detailin FIG. 10A, and include three side pieces 159 forming a triangle, andarms or flanges 161 orthogonal to the plane of said triangle forengaging respective cables 27. Flanges 161 or side pieces 159 or both,are made of electrically non-conductive material. Cables 27 are capableof conveying electrical power, are of lightweight as explained below,and have a high tensile strength. The preferred construction and mannerof employment of spacer assemblies 158 is shown in FIG. 10A. Extendingfrom each of cables 27 are adaptive connectors 501 (each similar to anadaptive connector 247 discussed below). Adaptive connectors 501 areprovided along each primary cable 27 at spaced intervals, connectors 501being in alignment along respective cables 27. Each adaptive connector501 has a pair of spaced, parallel aligned flanges 503 generallyradially (but not exactly radially since they clamp loops of wireextending from the respective cables 27) adjacent respective cables 27.Flanges 503 each have a pair of columns 505, 506 of holes, each columnof holes 505, 506 on each pair of flanges 503 being in alignment. Thecolumn of holes 506 being closest to respective cables 27 are attachedto cables 27 as explained later with respect to an adaptive connector247. A set of lugs (not shown) extend through the respective alignedholes 505 and also holes in alignment on respective orthogonal flanges161 to attach each corner of respective spacer assemblies 158 torespective primary cables 27. Each arm 159 of the respective spacerassemblies 158 has an enlarged portion 520, preferably of tubularconstruction for stiffness and resistance to buckling, extending betweenadjacent primary cables 27, which have shoulders or tapering surfaces522 to help restrain movement of cables 27 with respect to each other,and to create a lateral clearance between spacer assembly 158 and eachcable 27. Arms 159 have smaller end portions 524 for attachment to eachother and to respective orthogonal arms 161. Spacer assemblies 158 canhave various configurations; spacer assemblies 158 are shown havingsquare cross sections, but circular cross sections are alsoadvantageous. Spacer assemblies 158 can each be one piece, being bentinto their triangular shapes and slipped onto three primary cables 27,or arms 159 can be welded together before or after installation oncables 27. Arms 159 are preferably welded to spacer assemblies 158although bolted connections are possible.

At the uppermost part of the rocket launch system 1 is the set oflighter-than-air, tensioning balloons 160 (FIGS. 1, 1B, 12-14), andthere are other lighter-than-air tensioning balloons 164 (FIGS. 1, 1B,11, 15, 17, 18, 21) positioned along the cables 27 for offsetting theself weight of cables 27 and somewhat contributing to their tensioning.Balloons 160 are connected to a tensioning balloon attachment frame ortop large harness 162 (shown in FIGS. 12-14) for the purpose ofsupporting part of the weight of the primary cables 27 and allcomponents above other tensioning balloons 164, docking station 166(FIG. 13 discussed below), inclusive of the operational weight of acarriage 20 with a flight ready rocket 18. Balloons 160 and 164 mustaccommodate any lift fluctuations and reaction forces due to themovement of carriage 20 and its contents, and other components. Thereare variations in lift from tensioning balloons 160 and 164 due to dailythermal and atmospheric pressure variations. An additional amount oflift is required to cause primary cables 27 to be tensioned to asignificant part of their safe working load, since cables 27 must bekept as close to vertical as practical. As noted, one or more additionalsets of lighter-than-air balloons 164 or 164A (FIGS. 1, 11, 15, 16, 17,20A, 20B), which can be smaller than lighter-than-air balloons 160, mustbe interspersed along cables 27 to relieve the self weight of cables 27and the weight of the supporting structure and spacer assemblies 158 ofprimary cables 27 together with daily thermal lift variations with amargin of safety to prevent cable breakage under self weight, the neteffect being that cables 27 with associated balloons approximate cableswith no weight or negative weight. Primary cables 27 are engaged by andprovide power to a winch or hoist 169 discussed below, and form acableway path 170 shown in FIGS. 11 and 13. Cableway path 170 is formedof and enclosed by primary cables 27, which carriage 20 engages and fromwhich derives power so it can travel along cables 27. Tensioning balloonattachment frame 162 is composed of an upper ring 145 and a lower ring146 (FIGS. 13-14) which are counter rotational, about a rotary bearing149. Upper ring 145 and lower ring 146 are driven by a geared rotationaldrive system 177, and are described below.

Docking station 166 is shown in FIGS. 13 and 14. Docking station 166 hasupper ring part 172 which can be rotated with respect to a lower ringpart 174, parts 172 and 174 being engagable with a ring bearing 176, aredriven by a geared rotational drive system 147 (also see FIG. 28 for acorresponding rotational drive system 379), which includes and isassisted by reaction force thrusters 178. Geared rotational drivesystems 177 and 147 are also used to provide the opposed rotation ofupper ring 145 with respect to lower ring 146 of tensioning balloonattachment frame 162, and also of upper ring part 172 and lower ringpart 174 of docking station 166 mentioned above. The rotational drivesystems 177 and 147 of tensioning balloon attachment frame 162 anddocking station 166, respectively, are coordinated so that allcomponents between and inclusive of, upper ring part 172 and lower ring146 rotate together as a unit, with associated cables kept from twistingaround each other. Force thrusters 178 and 148 counter wind inducedrotation or rotation resulting from the rotation of a carriage 20, whenthe lower end of carriage 20 is held within upper ring part 172 ofdocking station 166, and carriage 20 is being rotated into an optimaldirection for launch. Docking station 166 has two sets of three internalcarriage guides 180A, 180B (FIGS. 13, 14) for entering radial recesses130 of each carriage 20 to keep the respective carriages 20 in properalignment and stable, while supplying electrical power to the carriagetraction drives 26.

Still referring to FIGS. 13 and 14, lift ring assembly 182 is shown.Lift ring assembly 182 includes a short tubular lift ring 183 with atriangular or possibly circular cross section, and is guided by and iselectrically connected to secondary cables 184 extending upwards fromupper ring part 172 of docking station 166 to connect to lower ring 146of tensioning balloon attachment frame 162. Tertiary cables 186 (FIGS.13, 14) extend upwardly from lift ring assembly 182 to the frame of alower hoist 198. Lift ring assembly 182 is guided by and deriveselectrical power from secondary cables 184 which are connected todocking station 166. Lift ring assembly 182 is supported by tertiarycables 186 which are connected to a lower hoist carrier 200 which is theframe of lower hoist 198. Referring to FIG. 14A, carriage end gripper196 is provided with a set of four orifices 195 through which secondarycables 184 freely pass, and a pair of orifices 197 through whichtertiary cables 186 freely pass. Electrical power for a carriage endgripper 196 can be provided by secondary cables 184.

Tubular lift ring 183 has a set of inwardly extending guide structureelements or internal carriage guides 188 which are engaged in therespective three recesses 130 extending longitudinally in carriage 20for maintaining the orientation of carriage 20 in tubular lift ring 183and supplying power to carriage 20. Lift ring assembly 182 comprisestubular lift ring 183, a carriage pivoting assembly 189 which itselfincludes a pair of opposing pivot pins 190 and a rotational drive system194, lift ring guides 192 and reversible traction drives 193. Rotationdrive system 194 rotates tubular lift ring 183 which is pivotable aboutthe horizontal axis defined by pins 190. The center of gravity oftubular lift ring 183 is made to fall in its geometric center which isco-incident with the axis of pins 190. Tubular lift ring 183 has aclamping or locking mechanism 996 (shown schematically in FIGS. 13 and14) to permit it to be releasably attached to carriage 20 in such amanner that center of gravity 36 of carriage 20 is held on the axis ofpins 190. The axis of rotation of reversible variable pitch thruster 31is made parallel to the horizontal axis defined by pins 190. Tertiarycables 186 are respectively connected to the respective lift ring guides192. Tertiary cables 186 are provided in two groups of cables of fixedlength, and are attached to lower hoist carrier 200 180° apart, toconnect carrier 200 to lift ring guides 192 below and assist in guidingthe movement of carriage end gripper 196 (discussed below), and carrieselectrical power if needed.

Lift ring assembly 182 includes rotational drive system 194 to changethe elevation angle indicated by the arrow P (FIG. 13) of tubular liftring 183 and carriage 20 held thereby with respect to cables 184 and186. Carriage end gripper 196 is also shown in FIGS. 12, 13 and 14.Carriage end gripper 196 can be supported/by a lower hoist cable. 201attached to lower hoist assembly 198 mounted on lower hoist carrier 200.Lower hoist cable 201 moves in the directions indicated by the arrow Qin FIG. 14. Carriage end gripper 196 is guided in motion by secondarycables 184 which carry electrical power and are supported by tertiarycables 186. Carriage end gripper 196 is able to releasably lock to thetop of a carriage 20 by means of locking pins 204 which cooperate withpin lock receptacles 32 in the upper part of carriage 20. When carriageend gripper 196 is firmly connected to carriage 20, carriage end gripper196 is able to lift or assist in lifting carriage 20 from dockingstation 166 and up through lift ring assembly 182 until center ofgravity 36 of carriage 20 coincides with the horizontal pivot axis oflift ring assembly 182 defined by pins 190 when lift ring assembly 182is lowered into contact with upper ring part 172 of docking station 166.The length of cables 186, which guides the motion of end gripper 196must be long enough to permit carriage 20 to rotate about the horizontalaxis when end gripper 196 detaches from carriage 20 and is lifted ashort distance out of engagement with docking assembly 166.

Lower hoist assembly 198 is fixed to the lower end of lower hoistcarrier 200 as noted above, and also as noted above is used for liftingor assisting the traction drives 26 of carriage 20 in moving carriage 20into and out of engagement with tubular lift ring 183. Lower hoistcarrier 200 is raised and lowered as indicated by arrow R on hoistcables 202 from upper hoist 168 attached to tensioning balloonattachment frame 162 shown in FIGS. 12, 13, and 14. Power is provided tohoist 169 through secondary cables 184. Either three-phase current ordirect current can be used to power hoist 169. In the three-phasecurrent system as shown, the group of four secondary cables 184, furtheridentified (FIG. 14) from left to right as cable 184A is phase one ofthree, cable 184B is phase two of three, cable 184C is phase three ofthree and 184D which may be used as an electrical neutral or as aduplicate of phase one of three. Also as noted earlier, lighter-than-airballoons 160 support the upper components of rocket launching system 1and provide a significant portion of the tension required to keepprimary cables 27 and secondary cables 184 in tension so as to make themtaut, even with operational loads. As shown in FIGS. 12, 13 and 14,tensioning balloon attachment frame 162 is disposed beneathlighter-than-air or tensioning balloons 160.

Referring to FIGS. 1, 1B, 11, 15, 16, 17, 20A and 20B, these figuresshow a number of groups of smaller lighter-than-air balloons 164 or 164Aused to relieve the self weight of cables 27 and associated supportstructures and spacer assemblies are shown. Balloons 164 are tapered andballoons 164A are cylindrical, although other shapes and configurationsare possible and fall within the scope of the invention. Each of anumber of large harnesses 206 having tensioning balloon holders 208 isattached to primary cables 27 by means of a three-sided lower spacer orstabilizer assembly 210. Each lower spacer assembly 210 is constructedand attached to primary cables 27 in the same manner as spacers 158 wereconstructed and employed as described earlier. Balloons 164 or 164A arerespectively connected to balloon holders or attachment points 208 (FIG.18). Lower spacer assembly 210 has three arms 211 forming an equilateraltriangle as viewed in plan, arms 211 being parallel to respective arms222 of large harness 206. Lower spacer assembly 210 has connectingstructure 214 at the respective intersections of arms 211, from whichleads 215 extend. Each lead 215 from lower spacer assembly 210 extendsfor attachment to the respective balloon holders 208 of large harness206. There are also provided a number of upper spacer or stabilizerassemblies 216 which, like spacer assemblies 210, separate primarycables 27 and further hold in place cable ties 218 and 219. Upper spacerassemblies are constructed and employed as are spacer assemblies 158 andlower spacer assemblies 210. Each upper stabilizer 216 has three arms217 forming together in a plan view, an equilateral triangle, arms 217being parallel to respective arms 222. A cable connector 220 is at theintersection of the respective arms 217. Pairs of stabilizing ties 218are connected at one end to a cable connector 220 at opposite ends ofarms 217 and to tie holders 221 at the midpoint of arms 222 parallel torespective arms 217. Another set of cable leads 219 is connected betweentie connectors 220 and balloon holders 208. This arrangement assists inholding harness 206 stably in place. Harnesses 206 are installedperiodically with balloons 164 and 164A, respectively, along the lengthof primary cables 27 to compensate for the self weight of cables 27 andany attached structures, and to induce tension in the cables to assistin keeping them upright. Considering balloons 164, these are shown inFIGS. 11 and 20A, and have generally an upper spherical cap, a lowerspherical cap (but inverted) with a smaller diameter than the upperspherical cap, and tapered sides connecting the upper spherical cap andthe lower spherical cap. The lower portion could have a basically zerodiameter, which is more typical of lighter-than-air balloons. This typeof balloon can be referred to herein as conical balloons. Referring toballoons 164A shown in FIG. 20B, these each comprise an upper sphericalcap, a lower spherical cap (but inverted) with the caps having equaldiameters. The upper and lower caps are connected by cylindrical sides.This type of balloon can be referred to herein as cylindrical balloons.Considering tensioning balloons 160 as in FIGS. 12 and 28, theseballoons have upper spherical caps and conical sides terminating attheir lowest portion at essentially a point. These are also conicalballoons.

A specific assembly for connecting the various components of upperspacer 216 is as follows. Upper spacer assembly 216 and the itemsconnected to them are shown in FIGS. 15A, 15B and 15C. As noted above,upper spacer 216 is composed of three arms 217 forming an equilateraltriangle. Referring to FIGS. 15B and 15C, cable connector 220 comprisesa base plate 902 having a central arm 904 and two arms 906 and 908separated from central arm 904 by an angle exceeding 90°. Cableconnector 220 further has a support portion 910 which is generallyopposite arm 904. Base plate 902 is advantageously flat, and extendingperpendicularly thereto is a cable connecting flange 912 which extendsalong the middle of support portion 910. A pair of arm support flanges914 and 916 also extends perpendicularly from base plate 902 and areequiangularly spaced from cable connecting flange 912. Arms 904, 906 and908 have lug-receiving holes 920, 918 and 922 respectively, extendingperpendicularly through the respective arms 904, 906 and 908. Cableconnecting flange 912 has a series of equally spaced, lug-receivingholes 924 extending along the height of flange 912.

Each cable 27 has at least one, and more likely many, connectingstructures 925, each connecting structure 925 being composed of pairs ofparallel, opposing, spaced flange-receiving connecting flanges 926, 927which are parallel to the respective axes of cables 27. Flange 926 hasparallel aligned columns of lug-receiving holes 928 and 930, which arealigned with corresponding holes 928, 930 on the other flange 927. Inorder to attach each cable connector 220 to a position on a respectivecable 27, cable connecting flange 912 is inserted betweenflange-receiving connecting flanges 926, 927 with holes 924 in alignmentwith each of the respective holes 928. A set of lugs 932 is insertedinto the respective aligned holes 928 and 924 and attached to a nut orother fastener receiver 933. To further connect respective cableconnectors 220 to respective cables 27, similar bolts 256 as shown inFIG. 22 are used to clamp loops 244 of cable 27. Flange-receivingconnecting flanges 926, 927 are close enough to each other to enabletraction drives 26 to engage respective cables 27 as carriages 20 withtraction drives 26 pass flanges 926 and 927 in full operative engagementwith respective cables 27.

As noted earlier, pairs of stabilizing ties 218 connect cable connector220 to respective midpoints of a pair of arms 222 of large harness 206.Each stabilizing tie 218 has at one end a connecting yoke 934 with apair of parallel flanges 936 with aligned holes 938 through whichextends a lug 940 which also passes through hole 908 for subsequentreception by a nut or other fastener receiver 942 to connect stabilizingtie 218 to cable connector 220. Similarly, cable tie 219 has a couplingyoke 944 with a pair of parallel flanges 946 with a pair of alignedholes 948. Arm 904 is inserted between flanges 946, and a lug 950 isinserted in holes 948 and 920, and into a nut or other fastener receiver952.

FIG. 15E shows a detail of the connection of lower spacer assembly 210(FIG. 15) to cables 27 and to large harness 206 by means of connectingstructure 214. The pair of connecting structures 925 is affixed to cable27 by engaging loops 244. Connecting structure 925 is composed of avertical flange 960 having a connecting flange 962 extending therefromand including a column of lug holes 963. A set of arm support flanges966 extends from vertical flange 960 to which they are welded by anappropriate welding procedure, and are respectively connected torespective arms 217 of lower spacer assembly by an appropriate weldingor other procedure. Arm support flanges 966 are angled from each otherand angled where they engage respective arms 217 to provide astructurally strong support. Connecting flange 962 is placed between theparallel flanges of connecting structure 925 with the holes beingaligned with holes 928 (see FIG. 15B) and lugs 932 and inserted throughrespective aligned holes of connecting flange 962 and holes 928 andthrough nuts or other fastener receiver 933 (see FIG. 15A) to secureconnecting structure to cable 27.

Vertical flange 960 has a finger portion 968 through which extends ahole 970. The end of each lead 215 for attaching lower spacer assembly210 to large harness 206 has a coupling yoke 972 composed of parallelflanges 974, 976 through which extend aligned lug-receiving holes 978.Yoke 972 is moved so that finger portion 968 is inserted between flanges974 and 976 with holes 970 and 978 being aligned. A lug 980 is insertedthrough holes 970 and 978, and into a nut or other fastener-receivingmeans 982.

It was mentioned earlier that stabilizing ties 218 were connected to themidpoint of arms 222. Apparatus for doing this is shown in FIG. 15D. Atie-connecting flange 984 is attached to and extends from the midpointof each of arms 222. Flange 984 has two short arms 986, each having alug-receiving hole 988. Each tie 218 has connecting yoke 944 withflanges 946 as discussed above. Yokes 944 from each tie 218 are slippedover an appropriate arm 986 of flange 984, and a lug is inserted throughholes 948 and 988 and tightened in place with a fastener such as with anut.

Structure for attaching each of the harnesses, spacers and stabilizersis preferably composed of the same type of components and subcomponents.This type of structure is strong, stable, easy to fabricate and put intouse.

A number of three-sided upper spacer or stabilizer assemblies 260,virtually identical to spacer assemblies 210, are located above largeharness 206 (as shown in FIG. 18). The detailed construction of spacerassemblies 260, and how it is attached to primary cables 27, isvirtually the same as spacer assemblies 158 and lower spacer assemblies210. Spacer assemblies 260, as shown in FIG. 18, is attached to cables27 by means of connecting structures 262 at the intersection of pairs ofconnected arms of the three arms 264 which form an equilateral triangle.A set of lightweight cables 266 (as compared to relatively heavy weightcables 27), extend from connecting structure 262 to balloon holders 208,which are constructed to hold them to large harness 206. Lightweightcables 266 support large harness 206 during assembly of the launchsystem or during maintenance of balloons 164.

A set of three electric reaction thrusters 800 are respectively attachedto rotatable support joints 802 at the intersection of respective arms222, as depicted in FIGS. 18 and 19. Each thruster 800 comprises a fan804 which are each mounted in a fan housing 806. Each housing 806 ispivotably mounted between a pair of arms 808. Each arm 808 has coaxialpivot pins 809 extending into housing 806, enabling each housing 806 topivot about an axis S-S in the direction of the arrows T both clockwiseand counter clockwise. Arms 808 branch from a central arm 810, which isattached to rotatable support joints 802 as discussed above. Thrusters800 are gimballed electric thrusters. Thrusters 800 are pivotable androtatable, and are operated to hold the launch system 1 oriented withrespect to the vertical as required. Thrusters 800 compensate for windforces and for the partial or total deflation of any balloons 164 untilthey can be replaced or otherwise maintained. The position of largeharnesses 206 with respect to the base of launch system 1 is controlledby position sensors 812, which could be a global positioning system(GPS) for supplying position reference data to the computers controllingthe direction and force of thrusters 800.

The following is an explanation of the matter in which balloons 164(which would apply to balloons 164A) are attached to the primary cables27 is shown with respect to FIGS. 15, 16, 17, 18, 20A and 20B. Spacerassembly 260, together with lightweight cables 266 shown in FIG. 18,located above upper stabilizer 216, has been omitted for clarity in FIG.15. Viewing FIG. 15 first, a portion of primary cables 27 is shown, withlower stabilizer 210 and upper stabilizer 216 being provided tostabilize upper harness 206. Three balloons 164 (only one of which isshown in solid lines in FIG. 15) are provided for offsetting the selfweight of cable 27, various stabilizers, and any excess loads applied tocables 27. Depending on their diameter, balloons 164 may require tubularseparators made of the same material as the balloons and inflated withthe same lighter-than-air gas. In order to keep cables 27 from touchingballoons 164 (or balloons 164A), stabilizing straps or webbing 227 (FIG.15A) are provided for attaching balloons 164 to cable separators such asupper spacer assembly 260 (FIG. 18) to prevent such contact. Eachstabilizing strap 227 is part of a stabilizer 228 which is connected toeach of cables 27 in the same manner that other stabilizers are attachedto cables 27. Stabilizers 228 further have a connecting member 229 forholding the respective stabilizing straps 227 in place. The manner inwhich the foregoing is done can be seen in greater detail in FIG. 16,which is a top view taken in the direction 16-16 in FIG. 15. It can beseen that each stabilizer 228 is attached to primary cables 27 withinthe three intersections of stabilizer 228. Stabilizer 228 is composed ofthree respective arms 234, which collectively intersect to form anequilateral triangle. From each connecting member 229, a pair ofstabilizing straps 227 forms an angle so that the respective pairscontact the respective balloons 164, to which they are nearlytangential. Straps 227 are each attached to a balloon 164 by atangential strap connection 224. Strap connections 224 prevent cables 27from contacting balloons 164 (or balloons 164A). Strap connections 224(FIG. 15) can advantageously be an appropriate adhesive, plastic weldingor stitching with an adequately strong thread, for connectingstabilizing straps 227 to respective balloons 164 (or balloons 164A).

FIG. 17 shows three balloons 164 attached to large harness 206 atballoon holders 208. Upper stabilizer assembly 216 is shown having itsstabilizing cable ties 218 connected to tie holders 221 on arms 222.Force vectors FF are shown in FIG. 17 extending along tensioning cable219, showing tension forces extending from cable connectors 220 toballoon holders 208.

A side view of the attachment system is shown in FIGS. 20A and 20B. Eachballoon 164 (FIG. 20A) and 164A (FIG. 20B) has light, strong, tensionbasal connectors 232 connected to a balloon holder 208 of large harness206. One or more of connectors 232 may be tubular to carry replacementlighter-than-air gas into each balloon 164 to compensate for leakage.Balloons 164 and 164A are lighter-than-air balloons, so the tensileforces FF are as shown by the arrows along connectors 232. Connectors232 are tangent to the skin of each balloon 164 and 164A. A set of threeor more connectors or stabilizers 228 (FIG. 16) are shown for connectingthe respective balloons together at several points.

As explained earlier, tensioning balloons attachment frame 162 has upperrotating part 145 and lower rotating part 146 (FIGS. 13, 14), which areconnected through ring bearing 149 on the vertical axis for reducing thefriction from the rotational movement as depicted in FIG. 12. Reactionforce thrusters 148 are tangentially attached to the periphery of upperrotating part 145. Similarly, reaction force thrusters 178 are attachedto the periphery of lower part 174 of docking station 166. Thepropulsive units mounted on upper rotating part 145 and those mounted onpart 174 are used to maintain them non-rotatable. The propulsion unitson upper part 145, in conjunction with geared rotational drive system177, assist the rotation of the lower rotating part 146 relative toupper rotating part 145. Similarly, the propulsive units on lower part174, in conjunction with geared rotational drive system 147 (FIGS. 13,14), assist the rotation of the upper rotating part 172. Secondarycables 184 collected in two groups are attached opposite each other(180° apart) on lower rotating part 146. Upper hoist 169 is attached tolower rotating part 146. Cables 184 connect balloon attachment frame 162to docking station 166 (FIGS. 13, 14) and carry electrical power asneeded. Cables 184 also guide movement of lower hoist carrier 200,carriage end gripper 196 and lift ring assembly 182. Cables 184 are longenough to safely allow a period of downward acceleration at the localacceleration due to gravity of lower hoist carrier 200 and itemssuspended therefrom, sufficiently long for a rocket 18 to bedisconnected from its restraint while in freefall conditions and boostedclear of carriage 20. An additional length of cables 184 to allow anadditional period of time is also required for the deceleration for therest of lower hoist carrier 200 and all items (including loaded or emptycarriage 20) suspended therefrom. An additional length of cable wouldpermit deceleration of a completely loaded carriage 20 to rest in theevent of a short duration booster misfire.

As explained above and further discussed below, a means is required forsecuring items of system 1 to the various cables. FIG. 21 shows a cable240 made of strands 242 of wire. Each strand 242 of cable 240 can havelooped-out portions or loops 244 extending from the outer surface of thebody of cable 240 for securing items to cable 240, while leaving themajority of the cable's outer surface unobstructed. Each loop 244extends out from the body of each cable 240 and returns into the body ofcable 240. For example, adaptive connector 247 is shown in FIG. 22 asdiscussed in detail hereafter. Adaptive connector 247 has an outstandingflange 248 having a series of bolt holes 249 and a further series ofbolt holes 250 extending through a pair of parallel walls 252 extendingin parallel form from a common base 253. Adaptive connector 247 can beurged against cable 27, with loops 244 slid between parallel walls 252and their respective loop holes 254 in alignment with holes 250. A bolt256 can be extended through loop holes 254 and bolt holes 250 to secureadaptive connector 247 to cable 27 and a nut can be put on respectivebolts 256 to effect a firm connection. A top view is shown in FIG. 23.Alternatively, parallel walls 255 separated by a spacer 259 as analternative adaptive connector 257 can be used, as shown in the top viewof FIG. 24. Cable 27 can be gripped by a pair of traction drive wheels26A of carriages 20 as shown in FIG. 25, rotating in opposite directionsO₁ and O₂.

In order to use the rocket launch system 1 described thus far, rockets18 are loaded in carriages 20, respectively in one of the apparatus asshown in FIG. 5, and transported along pathway 15 with a lateralconveying device 46. Lateral conveying device 46 is secured to elevatingassembly 60 using the respective tapered alignment pins 142 andfractional rotation twist lock pins 144 and their respective cooperatingalignment pin sockets 152 and fractional rotation twist lock pin sockets154, as explained with respect to FIG. 9. Secondary cables 184 andprimary cables 27 are held taut by means of tensioning balloons 160 andballoons 164, respectively, with balloons 164 contributing to thetension in primary cables 27. Tension to the cables below is transferredvia tensioning balloons attachment frame 162 and cable separation andfurther tension is achieved via large harnesses 206, spacers 158 andspacer 228 (FIGS. 11, 15 and 18).

Each carriage 20 is rotated into alignment with internal carriage guides133 and loaded into lower guide tube 124 (FIG. 8). The upper part oflower guide tube 124 is then tipped into engagement with the lower partof secondary guide structure 125 (FIG. 10) until lower guide tube 124engages stop 132 to align carriage guides 133 and 138 as discussedearlier. The traction drives 26 are then used to drive carriage 20 upcable 27 through docking station 166 into its upper part 172 andpartially into lift ring assembly 182, which is lowered by use of hoist169 so that lift ring assembly 182 engages with upper part 172 ofdocking station 166 (FIGS. 13, 14). End gripper 196 is lowered andproperly attached to the upper end of carriage 20. Lower hoist assembly198, powered by current in secondary cables 184 transferred from cables27, lifts carriage 20 further into engagement with lift ring assembly182 such that the combined centers of gravity of lift ring assembly 182,carriage 20 and rocket 18 coincide with the pivot axis of lift ringassembly 182. Lower hoist 198 thus assists traction drives 26 whichengage internal carriage guides 180A and 180B in lifting carriage 20upwardly relative to docking station 166. Then carriage end gripper 196disengages locking pins 204 from pin lock sockets 32 of carriage 20 andis lifted minimally clear by use of lower hoist assembly 198. Lift ringassembly 182 is guided by secondary cables 184 and supported by tertiarycables 186. Hoist 169 lifts carriage 20 further until the lower end ofcarriage 20 is no longer within the lower part 174 of docking station166 and is only within upper part 172. Geared rotational drive system147 within lower docking station 166 and geared rotational drive system177 with tensioning balloon frame 162 now rotate all components in acoordinated manner between ring bearings 176 and 149 into a directionsuitable for launching rocket 18. Thrusters 148 and 178 operatesimultaneously to keep the lower part 174 of docking station 166 andupper ring 145 of tensioning balloons attachment frame 162 from rotating(FIG. 14).

Hoist 169 next lifts carriage 20 entirely out of engagement with dockingstation 166 (carriage 20 holding rocket 18 must be lifted higher andhigher according to their combined weight) and as high as required intothe middle of short tubular ring 183 for the safe launch of rocket 18.Rotational drive system 194, in coordination with reversible variablepitch thrusters 31 extended 90°, rotates short tubular ring 183 withcarriage 20 into an appropriate angle with respect to the horizontalsuitable for launch. Reversible variable pitch thrusters 31 are beingused to assist rotary drive system 194 and to prevent carriage 20 fromoscillating about the horizontal axis through pins 190. When carriage 20is at the desired elevation angle for launch and stable, reversiblevariable pitch thrusters 31 are rotated further about their hinges toavoid contact with hot rocket gases.

Variations are possible to assist rotary drive system 194. This includesthe positioning and stabilizing of carriage 20 in lift ring assembly182, and in particular to prevent the oscillation of carriage 20 aboutpivot pins 190. Referring to FIGS. 13B-13C, there can be provided atboth ends of carriage 20 reversible variable pitch thruster 31 and apair of accompanying hub motors 822. Each thruster 31 and hub motor 822can be housed in one end of carriage 20 beneath an end cover 830. Eachthruster 31 has a set of rotatable blades 826 that are mounted in apivotable thruster mounting 828 at both ends of carriage 20. Eachmounting 828 is mounted on a hinge assembly 829 and is movable between arest position (shown in dotted lines in FIG. 13C and an active positionparallel with the longitudinal axis of carriage 20 (shown in FIG. 13C insolid lines) by means of a hydraulic actuator 832, which pivots about anactuator pivot 834. When thrusters 31 are in their active position, anairstream is created as shown by arrows U. This prevents oscillation ofcarriage 20. Hub motors 822 are reversible since the airstream can go inboth directions. Likewise, the pitch of blades 826 is variable to varywith variance of the ambient air in which blades 826 are rotating.However, when the engine of rocket 18 ignites, thrusters 31 can be movedat an obtuse angle as shown in dotted lines at the left-hand part ofFIG. 13C to avoid the short duration booster exhaust. The upper end ofthruster 31 is also moved to its obtuse position to enable the loadingof a rocket 18 into carriage 20. It should be noted that the inside ofcarriage 20 has continuous heat-and pressure resistant tube 836 runningfrom end-to-end to contain a rocket 18 therein. A set of three or morecentering supports 840 maintain the centering of each reversible,variable pitch thruster 31.

The upper end of hoist cable 202 (FIG. 14) is fed out from upper hoist168 and reversible traction drives 193 of lift ring assembly 182 beginto drive downwards, while in operative engagement with secondary cables184. Hoist cable 202 unreels and moves lift ring assembly 182, carriage20, rocket 18 and all other components supported by cable 202 downwardsassisted by drives 193 to overcome friction and air resistance, so thatthey are in freefall at an acceleration of 1 g, and rocket 18 becomesweightless with respect to carriage 20. There is a slight frictionmaintained in upper hoist 168 to maintain control during freefall, andto avoid any slack and any uncontrolled unwinding of cable 202. Prior tofreefall, retractable end covers 30 (FIGS. 9, 9C, 13, 13A) of carriage20 are opened (or end covers 830 shown in FIG. 13C are opened).Retractable arms 34 or 35 (FIG. 26) inside of carriage 20, which hadbeen holding rocket 18 in carriage 20, are retracted (as discussedbelow), and the short duration booster rocket motor of rocket 18 isignited to drive rocket 18 out of carriage 20. The short durationbooster rocket motor only operates within the heat and pressureresistant confines of carriage 20 to prevent damage to launching system1.

After rocket 18 has travelled sufficiently far on its ballistic path,its main motors can be safely ignited as required to avoid damage tolaunching system 1. The feeding out of the cables 202 from upper hoist168 (FIG. 12) is gradually stopped while reversible traction drives 193of lift ring assembly 182 (FIG. 13) are operated in a braking mode toprevent the further freefalling of carriage 20, lower hoist carrier 200,carriage end gripper 196 and lift ring assembly 182 (FIGS. 12, 13, 14).Reversible variable pitch thrusters 31 (FIG. 13C) may then be used toassist the rotation of carriage 20 into a vertical position before theyare retracted into the ends of carriage 20 and may be used to purge anyexhaust gases from the interior of said carriage before closing theweather covers 30.

Short tubular ring 183, of lift ring assembly 182 with empty carriage20, having been rotated into the vertical position (in preparation forrotation about the vertical axis, since the rotational moment of inertiais lowest when carriage 20 is in the vertical position), is then andlowered by means of upper hoist 168 in engagement with upper part 172 ofdocking station 166, shown in FIGS. 13 and 14. Carriage 20 and carriageend gripper 196 may then be brought together to lock carriage 20 tocarriage end gripper 196 before carriage 20 is lowered into engagementwith upper part 172 if additional support or guidance is needed. Thelower end of carriage 20 is then lowered into engagement with upper part172 of docking station 166. Lower part 146 (FIG. 14) of tensioningballoons attachment frame 162 and upper part 172 of docking station 166are next rotated so that the internal carriage guides 188 of lift ringassembly 182 (FIG. 13, 14) and internal carriage guides 180 of upperpart 172 come into alignment with cables 27 of docking station 166 (FIG.13). Hoist 168 then lowers carriage end gripper 196 to the top of liftring assembly 182 (FIGS. 12, 13, 14) and releases carriage 20. Lift ringassembly 182 also disengages from carriage 20.

Carriage 20 quickly drives down the cableway path 170 (FIG. 11) formedby primary cables 27 using regenerative braking to keep the downwardspeed of carriage 20 to a manageable level. The power returned toprimary cables 27 in this and other launching stations is transferred toanother launch system to supplement or replace the power required forthe elevation of another carriage 20 up its cableway path 170. A minimumgroup of four active launch systems is envisaged with a fifth acting asa ready spare used for light duties such as tourism or high altitudeskydiving utilizing special lightweight carriages until an activelauncher requires maintenance or a higher net rocket launcher rate isneeded. A combined launch rate of once per hour is believed to befeasible.

After empty carriage 20 re-enters secondary guide structure 125 (FIGS.1A, 2, 8, 10 and 11), it is further lowered until carriage 20 disengagesfrom secondary guide structure 125 and becomes centered in lower guidetube 124 at the point where the combined centers of gravity of carriage20 and lower guide tube 124 coincide with the rotational axis of lowerguide tube 124. Lower guide tube 124 is then returned to the verticalposition and carriage 20 is lowered onto an appropriately alignedlateral carrying device 46 atop elevating assembly 60. Lateral conveyingdevice 46 returns empty carriage 20 to blast resistant assembly bay 10for reloading or to storage racks 7 for replacement and refurbishing.Another pre-assembled rocket 18, carriage 20 and lateral carrying device46 can be loaded into system 1, and the next rocket 18 launched asdescribed above.

One possible construction of a retractable arm is retractable arm 34 inthe direction of arrow V for holding rocket 18 in carriage 20 as shownin FIG. 26. Rocket 18 has at least six equally spaced adjustable slots300 for receiving retractable arms 34, there being one arm 34 for eachslot 300.

Referring next to FIG. 27, alternate, different retractable arms 35 maybe provided. Each retractable arm 35 has a head member 302 for enteringone of slots 300, and a base member 304 from which extend opposing,coaxial pivot pins 306. A stem 308 interconnects head member 302 andbase member 304, and strengthening webs or braces 310 extend betweenbase member 304 and stem 308. Carriage 20 has an interior, blastresistant tube 312 having a cavity 314. Tube 312 has a pair ofprotecting doors 316 mounted on hinges 318 which can be positioned toclose part of cavity 314 (as indicated by the arrows W) or pivotoutwardly to open part of cavity 314 as shown in FIG. 27. Tube 312 alsohas a cavity-covering end door 320. Door 320 may have an airflowdeflector 322 for protecting doors 316, 320 and cavity 314, areinforcing spine tension member 324 and a pin holder 326 holdingcoaxial pivot pins 328 for entering pivot sockets 331 on approximatesides of side walls 332 defining part of cavity 314. Door 320 pivots onpins 328 between open and closed positions. Walls 332 also have pivotsockets 334 for receiving pins 306 of retractable arm 35.

Cavity-covering end door 320 further has a hydraulically retractable pin336 for moving in and out of a socket 338 located in an arm 340 of door320, and a hole 339 in stem 308. Door 320 also has parallel legs 342with aligned holes 344. Stem 308 of retractable arm 35 has an upstandingportion 346 with a slot 348 extending longitudinally in stem 308.Portion 346 extends between legs 342, and a slider pin 350 extendsthrough slot 348 and into each hole 344 to couple retractable arm 308 tocavity cover door 320. A hydraulic arm 352 has legs 354 with alignedholes 360 for going between a pair of legs 362 at an end floor 364 ofcavity 314, legs 362 having aligned holes 366, and legs 354 are held inplace by a pin 356 extending through holes 360 and 366. Another pair ofparallel legs 368 extends from a shaft 369 extending generally forwardlyfrom arm 352, and a pair of aligned holes 370 receive a pin 371. Doors316 are opened and closed by hydraulic or electro-mechanical means,coordinated with door 320.

The foregoing arrangement locks doors 316 and 320, which are shown inFIG. 27 in their open position, and head members 302 of each retractablearm 35 remain in the respective slots 300 in rocket 18. When rocket 18is in freefall with carriage 20 and becomes weightless with respect tocarriage 20, arms 35 are rapidly retracted into their respectivecavities 314 along with the rest of the assembly operating with arms 35,and doors 316 and 320 are closed just prior to ignition of a shortduration booster rocket 998 of rocket 18 as shown in FIG. 7. Each rocket18 can have small sets of wheels 372 to keep rocket 18 centered in tube312 during launch in the event the line of thrust is not exactly coaxialwith the internal tube of carriage 20 or does not pass through therocket's center of mass.

Another version of the invention, in addition to launching rockets, canbe used if a telescope is to be lifted to the top of the unit. Referringto FIGS. 28 and 28A, a telescope holding system 373 is shown. FIG. 28Ashows balloon 160 in reduced form. The components related to thetelescope are discussed below. System 1 has three primary cables 27which carry electric power, and are attached to a docking station 374.Docking station 374 has an upper part 376 which is rotatable in thedirection of arrow X relative to a lower part 378 using rotational drivesystem 379. Referring to FIGS. 28B and 28C, rotational drive system 147rotates upper part 376 and lower part 378 relative to each other bymeans of a ring bearing 850 having an inverted L-shaped member 852 incross section, with sets of ball bearings 854 and 856 in tracks 857, 858and 859, 860 in upper part 376 and L-shaped member 852, and lower part378 and L-shaped member 852, respectively.

The upper ends of cables 27 are held fast as shown. One cable 27Aextends at an angle through an opening 862 in lower part 378 and anappropriate clamping mechanism 864 for holding cable 27A fast. A secondone of cables 27 is shown as cable 27B, and it is held fast by anappropriate means to a flange 866, as further shown in FIG. 28C. Thethird one of cables 27 is similarly held fast. A motor 868 rotates agear 870. Gear 870 is sequentially connected to teeth 872 of upper part376 to effect the foregoing rotation as shown by arrow Y. A protectivehousing could enclose motor 868 and gear 870.

Three or more reaction thrusters 380 can be used, and they offset therelative rotation of parts 390 and 378 which are kept stationary whenthe alternate launching system depicted in FIG. 28 is used to launchrockets. Similar to other docking stations, a ring bearing 377 androtational drive system 147 are included between upper and lower parts376, 378 of docking station 374. Secondary cables 184 also carryelectrical power for operating the electrically powered components. Itcould be a two cable direct current apparatus or a four cable,three-phase apparatus.

A lift ring 382 drives up or down in the direction shown by arrows Z oncables 184. Lift ring 382 includes reversible traction drives 386, and astructure 387 for holding carriage 20 which is able to pivot in thedirection indicated by arrow AA and a rotary drive 381 to change theangle of lift ring 382 and carriage 20. An upper docking station 388 hasan upper part 390 normally held stationary and a lower part 392, beingrotatable in directions shown by arrows BB about a vertical axis usingrotary drive 381. A ring bearing 394 reduces the friction from suchrotation. A minimum set of three reaction force thrusters 397 countersthe tendency of upper parts 390 to rotate about the vertical axis.

A rigid elevator shaft or elevator tube 396 may carry special carriages398 each having a telescope CC built within, to a top mount 399. Aspecial lightweight carriage or carriages 20A could also be used fortransporting carriage 20 up elevator tube 396 to mount 399 aftertransfer from lift ring 382. A set of electricity carrying cables orrails could be mounted on the inside of elevator tube 396 which thewheels of carriages 398 or 20A would engage and also receive electricpower (as did wheels of traction drives 26 which engaged cables 27), toenable the transport of carriage 20A up and down the inside of elevatortube 396. Balloon(s) 160 are attached to or surround elevator tube 396as described earlier to provide sufficient tension to cables 184 toenable the transport of lift ring 382 with special carriage 398 holdingtelescope CC therein, as well as to support the cables themselves andthe apparatus attached to the cables.

Telescope top mount 399 includes a turret-like platform 402 upon whichis disposed a rotatable turntable 404, which rotates with respect tostationary upper part 390. A telescope-receiving hole 405 extendsthrough platform 402 and turntable 404 as shown in FIGS. 28A and 29.Mounting walls 406 extend from turntable 404. A telescope-holdingstructure or ring 408 clamps special carriage 398 with telescope CCtherein, with the center of gravity of carriage 398 disposed in thecenter of ring 408 which acts in the same manner as lift ring assembly182 but without traction drives. As shown in detail in FIG. 29, ring 408has coaxial pivot pins 410 which extend into sockets 412 of mountingwalls 406. Mounting walls 406, ring 408 and pivot pins 410 for atelescopic tilting structure 411 are provided. Therefore, carriage 398and telescope CC mounted within it can be tilted in elevation asdesired, and the rotation in azimuth shown by arrow DD of turntable 404directs carriage 398 and telescope CC included in any desired direction.Turntable 404 and platform 402 may be made independently rotatable inthe respective opposite directions shown by arrows HH and II (FIGS. 28A,29) with respect to elevator tube 396. This rotation is effected bymeans of a rotary drive 383, similar to drive 381. Platform 402 may haveradially adjustable weights to make its rotational moment of inertiaequal to the rotational moments of inertia of the assembly of turntable404 and parts above it so that when they are rotated in oppositedirections no net torque is applied to elevator tube 396 as turntable404 and parts above it are rotated.

Rocket launch system 1 can be used for a variety of purposes. Forexample, it could be used to launch a single man or basic rocket 601which has a steerable motor 603 as shown in FIG. 30, which is movable asindicated by arrows EE to steer rocket 601. A person or occupant GG isshown wearing a fluid filled launch or re-entry suit 605 with joints 607locked in an optimal aerodynamic upright position for launch and lockedfeet first onto the top of rocket 601, for resisting the g-force effectsof the firing of rocket 18 during launch. Suit 605 detaches from rocket601 as desired after rocket 601 stops operating and the joints of thesuit are unlocked, permitting the occupant GG to move freely. If thesuit is to be used for re-entry, a portion of the fluid surrounding theoccupant GG can be pumped through porous pads to cool by evaporation theexterior of re-entry suit 605 upon re-entry, feet first. (The samepumping operation and the cooling effect would apply at launch as well.)Rocket 601 with occupant GG in suit 605 mounted on top, should affordoccupant GG an excellent view during the launch phase. An aerodynamicfairing around suit 605 may not be required, unless when so configured,and the set of joints 607 are locked in position, aerodynamic drag isstill higher than necessary for optimal launch.

FIG. 31 shows a possible method for transporting tourists in suits 605or materials in rigid pods 608 releasably clamped to a core rocket 604.Main rocket 601 ceases its controlled launch at a period after itslaunch. Core rocket 604 is releasable from main rocket 601 uponcessation of the controlled launch of main rocket 601. A windshield 609can be used to protect tourists in suits 605 or pods 608 from highvelocity air as rocket 601 penetrates the atmosphere on its way to spacewhere the suits 605 or pods 608 may be released in the directionindicated by arrows JJ. Core rocket 604 may have a set of turntable fins602 which are turned in the directions KK by the directional controlsystem to steer rocket 601.

FIG. 32 shows an alternate pod 610 with a sled-like re-entry frame 616.Occupant GG wears launch or re-entry suit 605. Sled-like re-entry frame616 includes steering fins 619, and an aero-spike 611. Aero-spike 611has an extendable antenna-like configuration with a disc 613 serving asa forward shockwave initiator to yield a shockwave 615 for reducingaerodynamic heating of suit 605.

In FIG. 33, re-entry suit 605 with person GG is shown fitted into a morerocket-like shaped frame 617 with directional steering fins 618 andaero-spike 611. Frame 617 has disk 613 as discussed with respect to FIG.32. A guidance equipment and storage compartment may be located in theaft interior frame 617.

An appropriate space suit 605 is shown on person GG in FIGS. 34 and 35,also serving to accommodate g-force effects. Space suit 605 enablesoccupant GG to survive, remain conscious and be able to remain activewhile in an upright posture in a high acceleration environment. Forextended operations, this is achieved by immersing the occupant in afluid of approximately the same density as the body, within a rigid suitwith external electro-mechanical or hydraulic, servo-assisted, constantvolume joints. Space suit 605 has a helmet 650 (FIGS. 34, 34A, 34B, 36)surrounding the head of person GG, and a rigid outer shell 648. An innersuit 651 lies close to person GG, and an internal face mask 653 with avisor 655 is sealed to inner suit 651. A nontoxic fluid 656 (FIGS. 34,34A-34B) such as water fills the space between rigid outer shell 648 andinner suit 651. If fluid 656 is heated to a comfortable temperature,inner suit 651 may be omitted. There is a double seal 654 between innersuit 651 and face mask 653. Inner suit 651 could be skin tight aroundperson GG, and face mask 653 could be ventilated to or from an airsupply via an air supply tube 661. A leakage canal 652 is provided onface mask 653 of space suit 605 for draining water if there is leakageinto the space between the double seals surrounding the face of personGG. Water or other appropriate nontoxic fluid 656 fills the spacebetween inner suit 651 and outer shell 648, and face mask 653 and visor655 as shown in FIGS. 34, 34A and 34B. Person GG in space suit 605 canturn his head within helmet 650 while suspended in water 656. Space suit605 is of rigid lightweight construction; however, volumetric airflowsensors in face mask 653 or visor 655 could be provided to direct ahydraulic or electro-mechanical drive piston (explained below) to movein and out to match the change of volume due to breathing. Additionally,in order to match the breathing rate, that is, the change of volumedivided by the change in time, pressure sensors at various places(particularly near the chest) in space suit 605 keep the liquid pressureconstant by directing the piston in and out. The use of external highpressure hydraulic power assistance to permit person GG to move aboutfreely in suit 605 in high acceleration environments such as existduring launch or re-entry avoids the possibility of water or otherhydraulic fluid used to activate the joints of the suit from escapinginto the suit's interior which could crush occupant GG.

With respect to the piston, reference is also made to FIG. 35. Here,space suit 605 has water (or nontoxic fluid of an approximating thedensity of the human body) 656 filling the suit around person GG, and apiston 657 moves in and out of a cylinder 660, powered by high pressurehydraulic fluid or direct actuation of piston 657 by electro-mechanicalapparatus to vary the volume in suit 605 as required for normalrespiration.

The rigid outer shell 648 is typical of the construction of suit 605depicted in FIG. 34 and is shown in FIG. 36. Rigid outer shell 648 ofsuit 605 includes a pair of rigid sleeves, each containing internalsleeves 664 (only one is shown) each of which is made from open, elasticwebbing or a soft, open pore foam or webbing and a pair of rigid legseach having internal legs of the same construction as internal sleeves664. The internal sleeves and internal legs will hereinafter be referredto as “internal sleeves.” The pores should be large enough so as not toimpede significantly the flow of water through sleeve 664. Sleeve 664 isheld centered within suit 605 by means of weak elastic tendons 668attached at one end to suit 605, which extend across sleeve 664 and areattached to, and tangent to sleeve 664 to which they are attached at theother end. The tensions in elastic tendons 668 are sensed and used toprovide feedback to direct the powered joints of suit 605 to mirror themotions of occupant GG, keeping him centered within the suit. Anoccupant GG merely slips into suit 605 and slides his or her entire bodyinto typical sleeve 664. Suit 605 is a practical and efficient spacesuit to be worn by a person GG on rocket 601 or within rocket 18,particularly during the launch, boost and re-entry phases of flight.Outer shell 648 could have an ablative exterior material with insulationor heat resistant thermal insulation.

Other versions of a rocket are shown in FIGS. 37, 38, 38A and 39. Arocket 700 has an aerospace plane 702 with deployed, and folded lift anddirectional control structures 704 attached to the body shown in FIGS.37, 38 and 38A, and foldable in the directions shown by arrows LL and MMA lifting body type re-entry vehicle 706 is shown in its folded launchconfiguration in FIG. 38 with lift and directional control structures704 in folded condition. Lifting body type control re-entry vehicle 706with lift and directional control structures 704 foldable in the furtherdirection indicated by arrows NN is shown in FIG. 38A in the folded andunfolded configurations. Rocket 700 is primarily a military version ofrocket 18.

Referring to FIG. 39, a more typical rocket 720 is shown. Rocket 720includes a satellite or other payload 722 which is protected duringlaunch and flight by a pair of disposable aerodynamic shells 724. Afterrocket 720 has left the atmosphere, shells 724 are automaticallydetached in the directions indicated by arrows PP and preferably fallback to earth and the satellite or other payload 722 goes into space.Rocket 720 is primarily a commercial version of rocket 18.

The preferred embodiment described above can be achieved using presentlyavailable materials and products. The typical carriage, loaded with arocket, can be estimated to weigh 80 tons although greater weights arepossible. Each cable must be strong and electrically conductive. Itshould further be wear resistant to withstand the travelling of tractionwheels up and down the cables. Thus, cables 27 and 184 could have asteel exterior, with intermediary portion of aluminum, and a steel core.The cables could be multi-stranded with copper and steel strands andcopper coated steel strands or other suitable construction. For a 70 tonlift, the cables should be about ⅔ inch in diameter. Each of threecables could have 1.25 inch diameter, and the secondary cables shouldeach have a diameter of one inch.

As noted earlier, the weight of the cables is advantageously offsetperiodically. Steel cables having a diameter of 1.125 inches weigh about2.03 pounds per foot. A factor of safety of at least five should beused. A one inch diameter cable holds 120 tons at its breaking point.

The preferred gas for the balloons should be hydrogen, which is muchmore buoyant than helium and may be generated from water, while limitedsupplies of helium are primarily mined from natural gas wells. However,safety is an important factor. The higher in the atmosphere the balloonsgo, the risk of a lightning strike increases. Therefore, the turntable,lifting assembly and components above all should be insulated from theearth, electrically charged to the same electric potential as the highaltitude atmosphere to avoid attracting lightning, and the electricalpower supply inductively connected. The insulating parts of the rocketlaunch system could advantageously be made from ceramics or glasses.

The skin for the balloons should be light, strong and ultraviolet (UV)light resistant. There has been ample work done in such skins from thedesign and operation of dirigibles and other balloons recently.

The advantages of the present inventive rocket launching system overthose presently in use are quite apparent. The first stage of the SaturnV Rockets launched by NASA consumed 203,000 US gallons of RP-1 (refinedkerosene) and 331,000 US gallons of liquid oxygen (LOX) in a period of2.5 minutes. The present invention could have greatly reduced the amountof propellants to loft the same payload by lifting numerous smallerrockets using the electrically powered carriages with an equivalentpayload up the balloon supported cables to a desired height prior tolaunch. The present state of the art uses a tremendous amount ofnon-recoverable fossil fuel based energy. For example, the VirginGalactic White Knight Mothership uses tons of JET-A-1 kerosene fuel toreach its launch altitude for the Space Ship Two which uses a form ofrubber with a liquid oxidizer, and yields a black sooty exhaust. Solidrocket boosters often leave fluorine and chlorine compounds andpartially-burnt hydrocarbons amongst other dangerous residues in theirexhaust. All of these exhausts and residues pollute the atmosphere. Onthe other hand, the energy used in lifting the carriages in thepreferred form of the present invention is derived from renewablesources and a significant portion is recovered when the traction drivesswitch to their regenerative mode when the carriage goes back down thecableway.

Furthermore, the present invention will reduce the cost of space flightsufficiently to permit the removal of debris in the orbit around ourplanet and even permit the construction of an orbital shipyard. A vividexample of the hazards of orbital debris in space was the collision of anon-operational Russian Cosmos 2251 communications satellite with aU.S.-based mobile telephony satellite owned by Iridium on Feb. 11, 2008.Each satellite was travelling at an orbital speed of 17,500 miles perhour. The debris from this collision was estimated to amount to 500pieces. NASA has said that this debris from the collision has elevatedthe risk of damage to the International Space Station. The InternationalAssociation for the Advancement of Space Safety has proposed themandatory removal of non-operating satellites.

The present invention thus includes a set of cables supported bylighter-than-air balloons, which can be used for a variety of purposesin a very effective and efficient manner. When used to launch rockets,the amount of fuel required at launch is dramatically reduced since therockets are transported into the upper atmosphere before their enginesare operated. The rockets can be used for a variety of purposes, and dueto the reduced energy expenditure and the resulting cost reduction, suchuses as recreational sports using rockets, parachutes, small jetengines, or other apparatus could be economically feasible. Likewise,facilities for servicing satellites become more feasible and economic.Uses for high altitude platforms such as for telescopes could be atremendous benefit to scientists.

In the preferred embodiment discussed above, three cables were providedfor three-phase electrical power. It is likely each cable shouldtransmit exactly one third of electricity. In the event this cannot bedone or in the event there is a possibility it can be accomplishedduring use of the rocket launch system according to the invention,structure should be provided for either having a neutral line or else aground to get the necessary electrical balance amongst each of the threecables.

The present invention has many uses in addition to those describedabove. There is a tremendous amount of debris orbiting the earth fromthe many rockets driven into space. NASA has estimated that in 2009,there are about 14,000 objects which are being tracked by the U.S. SpaceSurveillance Network. Many of these objects threaten other devices whichmay pass through the respective orbits of these objects, sincecollisions could cause considerable damage. The present invention couldbe used to place debris catchers in orbits for recovering andde-orbiting such debris in an economical and safe manner or recyclingsuch items as may be reusable into useful structures in orbit.

The cables discussed herein were described as being of the general typeof rope composed of twisted strands of metal and shown as twisted into ahelix. These are wire ropes which are electrically conductive, and aresimilar to those used on cable cars, funiculars and aerial lifts.Different variations in the cables have been discussed as well. However,the term “cable” is not intended to be restricted to wire ropes. Cablescould also be rods of different sorts, coming in single lengths, joinedby various types of welding, or in a series of smaller links which arecoupled together to yield the desired length. The important feature ofwhatever cable is used according to the invention is that it be strong,electrically conductive and able to take the stresses and strains whichwould exist at elevated altitudes for transporting rocket transportingdevices and other apparatus as discussed herein. These rods or othertypes of cables may be modified in different respects, such as, forexample, to modify the surface or configuration of the surface of therods or other cables so that the system would operate more effectivelyand more efficiently when the rods or other cables cooperate with thetraction drives of the respective rocket transporting devices. Such rodscould have a cylindrical cross section or other cross sectionsdepending, for example, on the nature of the traction drives usedtherewith. Referring to FIGS. 40 and 41, a rod 990 is shown connectingflanges 992 attached at joints 994. Flanges have attachment holes 996.As required to attach spacers on other structures to the side of therods to allow bolted or other connections may be attached by means ofbonding, solid state or other forms of welding (e.g. friction welding,explosive welding, brazing, etc.) or joining as deemed fit. The rodscould be modified in other ways depending on such factors as the natureof the linkage of the respective rods, the electric conductivity of therods, the safety of the rods and the like.

The invention has been described in detail with particular reference tothe preferred embodiments thereof. However, variations and modificationswithin the spirit and scope of the invention may occur to those skilledin the art from the foregoing material and from the appended claims.

What is claimed is:
 1. A rocket launch system comprising: at least oneelectric power line for carrying electrical power from a source ofelectrical power from a remote electric power system on the earth, theelectric power being withdrawable along said at least one electric powerline, said at least one power line having a low end portion for beingpositioned at a low altitude and a high end portion for extending intohigh altitudes; at least one rocket-transporting device line fortransporting a rocket-transporting device between a low altitude and ahigh altitude, said at least one rocket-transporting device line havinga low end portion for being positioned at a low altitude and a high endportion for extending into higher altitudes; and lighter-than-airballoons connected to said at least one power line and said at least onerocket-transporting device line for holding said at least one electricpower line and said at least one rocket-transporting device line upwardsto a high altitude.
 2. A rocket launch system according to claim 1wherein said at least one electric power line comprises three electricpower lines and said at least one rocket-transporting device linecomprises three rocket-transporting device lines, and said respectivethree electric power lines and said respective three rocket-transportingdevice lines are integrally combined into three power and transportingprimary cables.
 3. A rocket launch system according to claim 2 whereinsaid three power and transporting primary cables carry three-phaseelectrical power.
 4. A rocket launch system according to claim 3 whereinsaid lighter-than-air balloons are operatively attached to said threepower and transporting primary cables intermittently along the length ofsaid three power and transporting primary cables to support cumulativelysaid three power and transporting primary cables, and any otherstructure carried by said three power and transporting primary cableswhich is utilized in the launch of a rocket.
 5. A rocket launch systemaccording to claim 4 and further including: at least one large harnessfor being operatively attached to said lighter-than-air balloons; saidrocket launch system further including; basal connectors extending fromsaid respective large harnesses to said respective lighter-than-airballoons to connect said lighter-than-air balloons to said respectivelarge harnesses, said respective basal connections being tangent to saidrespective lighter-than-air balloons.
 6. A rocket launch systemaccording to claim 3 and further including: respective sets of spacerassemblies located intermittently along said three power andtransporting primary cables, each of said set of spacer assemblieshaving cable-engaging structure for engaging each of said three powerand transporting primary cables of said three power and transportingprimary cables to maintain a spaced separation between said three powerand transporting primary cables, and wherein said lighter-than-airballoons are respectively, operatively connected to at least one of saidspacer assemblies.
 7. A rocket launch system according to claim 3 forreceiving a rocket-transporting device having a particular structure forholding a rocket, said rocket launch system further comprising: adocking station operatively connected to said three power andtransporting primary cables at a terminal position along the length ofsaid three power and transporting primary cables, said docking stationbeing structured to receive a rocket-transporting device as part of apreparation for a launch of a rocket being transported in arocket-transporting device.
 8. A rocket launch system according to claim7 and further comprising power and guiding secondary cables operativelyattached to said docking station and being extendable to a higheraltitude than the altitude of said docking station, said rocket launchsystem further comprising lighter-than-air balloons operativelyconnected to said power and guiding secondary cables for holding andtensioning said power and guiding secondary cables aloft above saidpower and transporting primary cables.
 9. A rocket launch systemaccording to claim 8 and further comprising: a lift ring assembly inoperative engagement with said power and guiding secondary cables forderiving electrical power from and being guided by said power andguiding secondary cables, said lift ring assembly being positionableabove said docking station and being both operatively engageable with arocket-transporting device disposed in said docking station for liftingthe rocket-transporting device out of said docking station, andcomprising a rocket-transporting device pivoting assembly for beingtilted to a desired rocket launch angle.
 10. A rocket launch systemaccording to claim 9 wherein said rocket-transporting device pivotingassembly is a tubular ring configured to surround and operatively engagea rocket-transporting device, and being tiltable to orient arocket-transporting device disposed in said rocket-transporting devicepivoting assembly and any rocket disposed in the rocket-transportingdevice to a desired launch angle.
 11. A rocket launch system accordingto claim 10 and further comprising: a lower hoist assembly located abovesaid lift ring assembly when said rocket launch system is in operation;a set of tertiary cables extending from said lower hoist assembly forbeing operationally connectable to and supporting said lift ringassembly; and a rocket-transporting device end gripper disposablebetween said lower hoist assembly and said lift ring assembly and beingoperatively attached to said lower hoist assembly, said end gripperbeing releasably and lockably engageable with a rocket-transportingdevice in said lift ring assembly, said lower hoist assembly liftingsaid end gripper for lifting a rocket-transporting device intoengagement with said rocket-transporting device pivoting assembly priorto the launching of a rocket from a rocket-transporting device disposedin said lift ring assembly.
 12. A rocket launch system according toclaim 7 and further incorporating: a launcher based on the ground forlaunching respective rocket-transporting devices, said launcherincluding: a turntable mechanism for receiving respectiverocket-transporting devices for delivering to said docking station, saidturntable mechanism comprising: a turntable base; and a turret assemblymounted on said turntable base, the low end portion of said power andtransporting primary cables being connected to said turret assembly, andmoving structure for transporting respective rocket-transporting devicesfrom and to said turret assembly along said primary cables.
 13. A rocketlaunch system according to claim 12 wherein said turret assemblycomprises: a rotatable turntable rotatable with respect to saidturntable base, said rotatable turntable comprising: a rotatableturntable orifice for receiving respective rocket-transporting devices;a lower guide tube mounted on said rotatable turntable, said lower guidetube comprising: a lower guide tube orifice alignable with and having asize corresponding to said rotatable turntable orifice, said lower guidetube receiving respective rocket-transporting devices, said lower guidetube comprising: lower guide tube carriage guides for locating therespective rocket-transporting devices in said lower guide tube orifice;a secondary guide structure comprising: an integral tube having anintegral tube orifice and internal carriage guides alignable with saidlower guide tube carriage guides; and primary cable connecting structurefor connecting said primary cables to said secondary guide structure;and a rotational drive system assembly for rotating said lower guidetube with respect to said secondary guide structure to align said lowerguide tube orifice and said integral tube orifice, and to align saidlower guide tube guide structure and said secondary guide structure;said rotatable turntable rotating said lower guide tube and saidsecondary guide structure in a desired direction for the movement of arespective rocket-transporting device.
 14. A rocket launch systemaccording to claim 13 wherein the respective rocket-transporting deviceshave respective longitudinal axes and a set of external recessesextending along the length of the respective rocket-transportingdevices, and said lower guide tube carriage guides and said secondaryguide structure are internal carriage guides for being received by theset of external recesses in the respective rocket-transporting devices.15. A rocket launch system according to claim 13 wherein one of saidturntable and said turntable base comprises: a perimetrical portion anda flat surface; a vertical, annular flange extending from saidperimetrical portion; and a horizontal, annular flange extending fromsaid vertical, annular flange and having an upper, lower and radialsurfaces of said vertical, annular flange rotatable about respectiveradial axes; wherein wheels are mounted for engagement by said turntableand said turntable base; and the other of said turntable and saidturntable base comprises: a vertical, annular, tubular part concentricwith the other of said turntable and said turntable base; and ahorizontal, annular flange extending from said vertical, annular tubularpart, said horizontal, annular flange and said other of said turntableand turntable base having surfaces for engagement by said respectivewheels for reducing the friction between said turntable and saidturntable base upon the relative rotation thereof.
 16. A rocket launchsystem according to claim 13 wherein each of said turntable and saidturntable base has a perimetrical end portion for receiving a rollingbearing, and one of said turntable and said turntable base furthercomprises a vertical, annular part extending from said perimetrical endportion and a horizontal, annular flange extending from said verticalpart and having annular bearing surfaces for receiving rolling bearings;and the other of said turntable and said turntable base comprises avertical, annular part concentric with the other of said turntable andsaid turntable base and a horizontal, annular flange extending from saidvertical, annular part, and having annular bearing surfaces; and rollingbearings disposed between said horizontal, annular flange and both ofsaid annular, horizontal flanges and said horizontal, annular flange insaid annular bearing surfaces; said rolling bearings reducing thefriction between said turntable and said turntable base upon therelative rotation therebetween and resisting axial compressive andtensile forces as well as forces perpendicular to the axis of rotationand combinations thereof.
 17. A rocket launch system according to claim13 wherein said turret assembly further comprises: a yoke including: apair of spaced apart arms pivotally mounted on said turntable; saidlower guide tube being pivotally mounted between said pair of spacedapart arms, said lower guide tube and said secondary guide structurebeing pivotally mounted between said pair of spaced apart arms, the axesof rotation of said turntable and said lower guide tube intersectingorthogonally.
 18. A rocket launch system according to claim 17 whereinsaid integral tube is located at a fixed distance from the common pivotof said integral tube and lower guide tube, said secondary guide tubestructure being counterbalanced about the horizontal pivot of saidsecondary guide structure, said secondary guide structure beingalignable with the upper end of said lower guide tube to render saidintegral tube and said lower guide tube coaxial, and said secondaryguiding structure and said lower guide tube guiding structure inalignment.
 19. A rocket launch system according to claim 13 wherein therespective rocket-transporting devices comprise: electrically poweredtraction drives for engaging said respective primary cables fortransporting the respective rocket-transporting devices; wherein saidlower guide tube guiding structure and said secondary guide structureare electrically energized to transmit electrical power to said tractiondrives.
 20. A rocket launch system according to claim 13 and furtherincluding: an elevating assembly for moving a rocket-transporting deviceinto said turret assembly, said elevating assembly being engageable withthe respective rocket-transporting devices for moving the respectiverocket-transporting devices into said turret assembly.
 21. A rocketlaunch system according to claim 20 wherein said elevating assemblycomprises: a hydraulic cylinder; a hydraulic piston operatively disposedinside said hydraulic cylinder; a hydraulic piston rod connected to saidhydraulic piston and being axially movable with respect to saidhydraulic cylinder; an upper swiveling assembly operatively mounted onsaid hydraulic piston for receiving the respective rocket-transportingdevices and aligning the rocket-transporting devices with said rotatableturntable orifice; and a rotary drive for rotating said upper swivelingassembly.
 22. A rocket launch system according to claim 21 wherein saidupper swiveling assembly comprises: a rotatable bed for receiving therespective rocket-transporting devices and rotating therocket-transporting devices to align the respective rocket-transportingdevices with said rotatable turntable orifice.
 23. A rocket launchsystem according to claim 22 wherein said upper swiveling assemblyfurther comprises a table portion mounted on said rotatable bed forreceiving for further conveyance respective rocket-transporting devices.24. A rocket launch system according to claim 23 wherein said elevatingassembly further comprises a non-rotating bed fixed to said piston rod;said rotatable bed being mounted on said non-rotating bed.
 25. A rocketlaunch system according to claim 24 wherein said upper swivelingassembly receives respective rocket-transporting devices from lateralconveying devices having a set of lateral conveying device wheels, andsaid table portion is associated with tracks located on the ground andaligned with the set of lateral conveying device wheels for enabling thelateral conveying devices to be received on said table portion of saidelevating assembly.
 26. A rocket launch system according to claim 25wherein the respective lateral conveying devices and said table portioninclude attaching structure for releasably attaching the respectivelateral conveying devices to said table portion, the lateral conveyingdevices, said table portion and attaching structure being located on theground.
 27. A rocket launch system according to claim 26 wherein saidattaching structure comprises: a selected one of the group consisting ofalignment pins and fractional rotation twist pins extending from theupper surface of said table portion for being received in correspondingsockets in the respective lateral conveying devices; and alignment pinsockets and fractional rotation pin sockets in said table portion forreceiving corresponding tapered alignment pins and correspondingfractional rotation twist pins extending from the respective lateralconveying devices.
 28. A rocket launch system according to claim 25 andfurther including: a pathway located on the ground and having a set oftracks engageable by the set of wheels of the lateral conveying devicefor conveying respective rocket-transporting devices to said tableportion for transfer to said elevating system.
 29. A rocket launchsystem according to claim 28 and further comprising: a rocket storagestructure located on the ground loading for rockets to be launched fromsaid rocket launch system, loaded in respective rocket-transportingdevices.
 30. A rocket launch system according to claim 29 wherein saidrocket storage structure comprising: storage racks separated byblast-resistant partition walls.
 31. A rocket launch system according toclaim 30 and further including: a rocket loading system located on theground for removing respective rocket-transporting devices from saidrocket storage structure; and assembly bays; said rocket loading systemmoving respective rocket-transporting devices to respective assemblybays.
 32. A rocket launch system according to claim 31 wherein saidrocket loading system comprises: a transverse loader movable on theground with respect to the respective assembly bays; a set of trackslocated on the ground upon which said transverse loader travels; and aguide assembly for guiding said transverse loader and components of saidtransverse loader.
 33. A rocket launch system according to claim 32wherein said transverse loader moves longitudinally with respect to theassembly bays, and said transverse loader comprises: an elevatorassembly on the ground movable transversely on said transverse loaderand vertically for receiving respective rocket-transporting devices at arelatively high elevation and lowering the respectiverocket-transporting devices into the respective assembly bays.
 34. Arocket launch system according to claim 33 wherein said guide assemblycomprises: wheeled trucks movable on the ground on said set of tracksand carrying said transverse loader along said set of tracks; and railslocated on the ground and extending across said transverse loader, saidelevator assembly being movable along said rails.
 35. A rocket launchsystem according to claim 34 and further including an elevator assemblywheeled truck for carrying said elevator assembly along said rails. 36.A rocket launch system according to claim 35 wherein said elevatorassembly includes: a guide support apparatus mounted on said elevatorassembly wheeled truck and extending in a vertical direction; and anelevator operatively coupled to said guide support apparatus, saidelevator having electro-mechanical structures for moving said elevatoron said guide support apparatus; said elevator assembly lifting rocketsand carriages from said storage racks and lowering the respectiverockets and carriages into said respective assembly bays; and saidtransverse loader moving respective rockets and carriages between saidracks and said assembly bays.
 37. A rocket launch system according toclaim 36 wherein the respective rockets include elevator assemblyattachment receptacles; and wherein said elevator assembly furthercomprises: a grasping assembly for operatively engaging the elevatorassembly attachment receptacles for respective rockets disposed in saidrespective assembly bays for enabling said elevator assembly to lift therespective rockets from said respective assembly bays.
 38. A rocketlaunch system according to claim 37 wherein said elevator assemblyfurther comprises: depending legs attached to said elevator, said legsbeing movable with said elevator at different locations around therespective rockets for operative engagement with the respectivereceptacles of the respective rockets; guides for guiding said dependinglegs into the respective receptacles; and leg attachment apparatus forreleasably holding said respective legs to the respective receptacles.39. A rocket launch system according to claim 38 wherein the respectivereceptacles include: fractional rotation twist-lock pin sockets; andsaid leg attachment apparatus comprises: fractional rotation twist-lockpins for securely and releasably attaching the respective rockets tosaid elevator assembly.
 40. A rocket launch system according to claim 36wherein said transverse loader further comprises stabilizing armassemblies mounted on said elevator assembly for engaging andstabilizing the respective rockets disposed in said elevator assembly.41. A rocket launch system according to claim 40 wherein saidstabilizing arm assemblies comprise arms with structure for engaging therespective rockets, and actuators attached to said respective arms foroperating said respective arms to engage and release the respectiverockets.
 42. A rocket launch system according to claim 41 and furthercomprising: a main pathway located on the ground and extending inoperative proximity to said rocket storage structure and said assemblybays; and rails located on the ground disposed in said main pathway uponwhich lateral conveying devices can move for transportingrocket-transporting devices.
 43. A rocket launch system according toclaim 42 and further including: bay pathways located on the ground andleading from said respective assembly bays to said main pathway; andrails located on the ground in said bay pathways for operativeintersection with said rails in said main pathway.
 44. A rocket launchsystem according to claim 43, wherein said assembly bays are locatedbelow ground surface, and have the shape of an inverted frustum and madeof a concrete material for limiting the effects of damage due to thedetonation of rocket propellant by deflecting the blast upwardly andlaterally.
 45. A rocket launch assembly according to claim 44 andfurther including slidable blast covers slidable over said respectiveassembly bays for protecting against damage in the event of anaccidental blast in said bay.
 46. A rocket launch system according toclaim 31 and further comprising lateral conveying devices for movingrocket-transporting devices between said rocket storage structure, saidassembly bays and said table portion, said lateral conveying devicecomprising wheels for operatively engaging said set of tracks.
 47. Arocket launch system according to claim 46 wherein the respectiverocket-transporting devices have a base end proximal a rocket containedin the respective rocket-transporting devices, and wherein said base endis stably received in said lateral conveying device to hold therespective rocket-transporting devices in an upright position, and saidrocket-transporting device is releasably locked in said receivingstructure.
 48. A rocket launch system according to claim 47 wherein saidlateral conveying device is located on the ground, and comprises alocking mechanism, and said locking mechanism comprises fractionalrotation twist-lock pins for locking a rocket-transporting device insaid receiving structure.
 49. A rocket launch system according to claim47 wherein said lateral conveying device comprises: independentlysteerable wheels; and a steering mechanism for moving said lateralconveying device on said set of tracks.
 50. A rocket launch systemaccording to claim 49 and further including loading apparatus located onthe ground for loading rocket-transporting devices onto said lateralconveying device, said loading apparatus comprising: a loading bedrotatable about an axis of rotation for receiving a rocket-transportingdevice; and a rotator operatively connected to said loading bed formoving said loading bed from a holding position for holding arocket-transporting device on said loading bed to a release position forenabling the rocket-transporting device to be displaced to a respectiveone of said receiving structures of said lateral conveying devices in anupright position.
 51. A rocket launch according to claim 20 wherein saidelevating assembly comprises an electro-mechanical elevating assembly.52. A rocket launch system according to claim 3 wherein each of saidthree power and transporting primary cables is a body of cable, saidbody of cable comprising: strands of wire having looped-out portionsextending from said body of cable for securing items to said primarycable, each looped-out portion exiting from and returning to said bodyof said primary cable.
 53. A rocket launch system according to claim 52and further including: an adaptive connector having aligned wallorifices therein; and a connector for extending through a pair of saidaligned wall orifices and one of said looped-out portions for connectingsaid adaptive connector to each of said three power and transportingprimary cables.
 54. A rocket launch system according to claim 52 andfurther including: a carriage for transporting a rocket along said threepower and transporting primary cables, said carriage including: tractionwheels for engaging said respective primary cables and rotating on saidrespective primary cables without contacting said looped-out portions topropel said carriage along said primary cables.
 55. A rocket launchsystem according to claim 3 and further comprising a main rocket forbeing controllably launched by said rocket launch system and a corerocket being carried with and releasable from said main rocket, and awindshield operatively connected to said core rocket for protectionagainst high velocity air.
 56. A rocket launch system according to claim3 and further including: at least one spacer assembly for maintaining aspaced separation between said three power and transporting primarycables, said primary cables having an adaptive connector comprising apair of spaced, parallel flanges extending generally radially from saidprimary cables at the same level for each of said three primary cables,said spacer assembly comprising: three generally straight arms forming agenerally equilateral triangle, said three generally straight arms beinggenerally coplanar and forming an intersection on opposite ends of saidrespective generally straight arms; an orthogonal flange disposed atsaid respective intersections and being generally perpendicular to theplane of said three generally straight arms and disposed between saidrespective pairs of spaced, parallel flanges extending from saidrespective primary cables; and attaching structure for connecting saidrespective orthogonal flanges and said respective pairs of spaced,parallel flanges extending from said primary cables.
 57. A rocket launchsystem according to claim 2 and further comprising a docking stationconnected to said three power and transporting primary cables at aterminal positioned along the length of said three power andtransporting primary cables, said docking station being structured toreceive a telescope conveying carriage, and a telescope-holding systemoperatively connected to said docking station.
 58. A rocket launchsystem according to claim 57 wherein said telescope-holding systemincludes a rotatable turntable.
 59. A rocket launch system according toclaim 58 wherein said telescope-holding system including a mountconstructed to hold a telescope.
 60. A rocket launch system according toclaim 59 wherein said telescope-holding system further comprises atelescope-holding structure for holding a telescope on said rotatableturntable.
 61. A rocket launch system according to claim 60 and furtherincluding a telescope tilting structure.
 62. A rocket launch systemaccording to claim 61 and further including an elevator tube forproviding a transport path for a telescope conveying-carriage forconveying a telescope to said mount, said mount being constructed tohold said telescope conveying carriage for placing the telescope inoperative position(s).
 63. A rocket launch system according to claim 62wherein said elevator tube further includes: electricity-carrying cablesor wheels for powering the telescope conveying carriage in said elevatortube.
 64. A rocket launch system according to claim 63 wherein saiddocking station has a lower part and an upper part rotatable withrespect to said lower part, and a rotational drive system for offsettingthe relative rotation of said lower part and said upper part.
 65. Arocket launch system according to claim 64 and further including: a ringbearing located between said lower part and said upper part for reducingthe friction between said lower part and said upper part; and whereinsaid rotational drive system comprises reaction thrusters for providingsaid offsetting.
 66. A rocket launch system according to claim 65 andfurther comprising: electrical power secondary cables extending upwardlyfrom said docking station when said docking station has been elevatedunder the influence of said lighter-than-air balloons; and a lift ringdrivable upwardly and downwardly on said secondary cables, said liftring including: traction drivers and carriage-holding structures forholding a telescope-conveying carriage, said carriage-holding structurebeing pivotal and rotatable with respect to said secondary cables toorient a telescope-conveying carriage held in said carriage-holdingstructure for entry into said elevator tube.
 67. A rocket launch systemaccording to claim 66 and further comprising: an upper docking stationconnected to said secondary cables, said upper docking stationcomprising: an upper part, a lower part, wherein said upper part andsaid lower part are rotatable in opposite directions about an imaginaryvertical axis, a ring bearing for reducing the friction between saidupper part and said lower part, and a rotational drive system forrotating said upper part and said lower part.
 68. A rocket launch systemaccording to claim 2 wherein said cables have a steel exterior.
 69. Arocket launch system according to claim 2 wherein said cables comprise:a steel exterior; and an interior composed of copper-coated steelstrands.
 70. A rocket launch system according to claim 1 and furthercomprising at least one rocket-transporting device for transporting arocket along said at least one rocket-transporting device line, each ofsaid at least one rocket-transporting device including: traction drivesfor driving said respective rocket-transporting devices along said atleast one rocket-transporting device line; and a motor-generator forderiving electrical power from said at least one electric power linewhen said traction drives require energy to cause said at least onerocket-transporting device to travel upwards on said at least onerocket-transporting device line, and for supplying electrical power tosaid at least one electric power line when said traction drives generateelectric power when said traction drives retard the downward motion ofsaid at least one rocket-transporting device as said at least onerocket-transporting device travels downwards on said at least onerocket-transporting device line under the influence of gravity.
 71. Arocket launch system according to claim 70 wherein said at least oneelectric power line and said at least one rocket-transporting deviceline are integrally combined into at least one power and transportingprimary cable, said at least one rocket-transporting device being drivenalong said at least one primary cable by said traction drives uponenergization by said motor generator.
 72. A rocket launch systemaccording to claim 71 wherein each of said at least onerocket-transporting device comprises: a carriage having an interiorcompartment configured to contain a rocket, the rocket being ejectablefrom said interior compartment during launch.
 73. A rocket launch systemaccording to claim 72 wherein said at least one power and transportingprimary cable comprises three power and transporting primary cables tocarry three-phase power, wherein each of said three power andtransporting primary cables carry one of the phases, and said motorgenerator is powered by three-phase electrical power.
 74. A rocketlaunch system according to claim 73 wherein said respective tractiondrives comprise: a set of traction drive wheels associated with eachsaid carriage for engaging said three power and transporting primarycables for transporting each said carriage along said three power andtransporting primary cables.
 75. A rocket launch system according toclaim 74 and further comprising: a docking station operatively connectedto said three power and transporting primary cables at a terminalposition along the length of said three power and transporting primarycables, said docking station being structured to receive each saidcarriage as part of a preparation for a launch of a rocket beingtransported in each said carriage.
 76. A rocket launch system accordingto claim 75 and further comprising: power and guiding secondary cablesoperatively attached to said docking station and extendable to a higheraltitude than the altitude of said docking station; and tensioninglighter-than-air balloons operatively connected to said power andguiding secondary cables for holding said power and guiding secondarycables aloft above said three power and transporting primary cables. 77.A rocket launch system according to claim 76 and further comprising: alift ring assembly in operative engagement with said power and guidingsecondary cables for deriving electrical power and being guided by saidpower and guiding secondary cables, said lift ring assembly beingpositioned above said docking station and being operatively engageablewith each said carriage disposed in said docking station for liftingeach said carriage out of said docking station, said lift ring assemblycomprising: a tubular lift ring; and a carriage pivoting assembly fortilting said tubular lift ring to a desirable rocket launch angle.
 78. Arocket launch system according to claim 77 wherein said tubular liftring is a hollow apparatus configured to surround and operatively engageeach said carriage, and being tiltable to orient each said carriage andthe rocket in each said carriage in a desired launch direction.
 79. Arocket launch system according to claim 78 and further comprising alower hoist carrier from which are extendable a set of tertiary cablesfor being operationally connectable to and supporting said lift ringassembly; and a carriage end gripper disposable between said lower hoistcarrier and said lift ring assembly and being operatively attached tosaid lower hoist carrier, said carriage end gripper being releasablylockably engageable with one said carriage in said lift ring assembly,said lower hoist carrier lifting said carriage end gripper for liftingeach said carriage into proper engagement with each said carriagepivoting assembly prior to the launching of a rocket from said carriagedisposed in said lift ring assembly.
 80. A rocket launch assemblyaccording to claim 79 wherein said carriage pivoting assembly isoperatively connected to said secondary cables, said carriage pivotingassembly traveling downward along said secondary cables in a freefallcondition, said secondary cables being of sufficient length to enable arocket in each said carriage to be boosted free and clear of each saidcarriage by a short duration booster rocket during the freefallcondition.
 81. A rocket launch system according to claim 79 wherein saidcarriage pivoting assembly is operatively connected to said tertiarycables, said lower hoist assembly releasing said carriage end gripperupon initiation of the launch of a rocket, and a rocket being launchedfrom each said carriage in said carriage pivoting assembly, renderingsaid tubular lift ring and said carriage pivoting assembly in a freefallcondition, said secondary cables being of sufficient length to safelyallow a time period of sufficient length at the local acceleration dueto gravity of said lower hoist assembly with a rocket-transportingdevice having a rocket disposed therein to be decelerated to rest in theevent of a misfire while said lower hoist assembly is in the freefallcondition.
 82. A rocket launch system according to claim 78 wherein eachsaid carriage has opposite ends, and wherein each said carriage furthercomprises: thrusters at each of said ends for reducing oscillation ofeach said carriage in said lift ring assembly.
 83. A rocket launchsystem according to claim 82 wherein said thrusters are reversiblevariable pitch thrusters.
 84. A rocket launch system according to claim83 wherein said reversible variable pitch thrusters each comprise: a hubmotor; and a set of blades extending from said hub motor for beingrotated in selectively opposite directions by said hub motor.
 85. Arocket launch system according to claim 84 and further comprising:pivotable thruster mountings rotatably mounted on the respective ends ofeach said carriage, said thruster mountings holding said hub motor andsaid blades and being rotatable from a rest position within each saidcarriage to an active position parallel to the longitudinal axis of eachsaid carriage.
 86. A rocket launch system according to claim 85 whereinsaid thruster mountings are rotatable about opposite ends of each saidcarriage between said rest position, said active position, and an obtuseposition away from the openings of said respective ends to avoid theimpingement of exhaust gases of rockets being launched from each saidcarriage and to enable loading a rocket into each said carriage.
 87. Arocket launch system according to claim 77 and further including atensioning balloons attachment frame operatively connected to saidsecondary cables, said primary tensioning lighter-than-air balloonsbeing attached to said tensioning balloons attachment frame forimparting sufficient tension to support cumulatively each said carriage,secondary cables and any other structure carried by said three power andtransporting primary cables which are utilized in the launch of arocket.
 88. A rocket launch system according to claim 87 wherein saidrocket launch system further comprises: a lower hoist assemblyoperatively attached to said tensioning balloons attachment framelocated above said lift ring assembly when said rocket launch system isin operation; a set of tertiary cables extending from said lower hoistassembly for being operatively connectable to and supporting said liftring assembly; and a carriage end gripper disposed between said lowerhoist assembly and said lift ring assembly and being operativelyconnected to said lower hoist assembly, said carriage end gripper beingreleasably and lockably engageable with one said carriage in said liftring assembly, said lower hoist lifting said carriage end gripper forlifting each said carriage into engagement with said carriage pivotingassembly prior to the launching of a rocket from each said carriagedisposed in said lift ring assembly; and an upper hoist assemblyattached to said tensioning balloon attachment frame and beingoperatively connected to said lower hoist assembly and to said power andguiding secondary cables, said upper hoist assembly drawing power fromsaid power and guiding secondary cables for selectively raising andlowering said lower hoist carrier assembly to lift or assist in liftingeach said carriage into and out of engagement with said lift ringassembly.
 89. A rocket launch system according to claim 88: wherein saiddocking station has connected thereto an upper ring part having an axisof rotation, a lower ring part coaxial with said upper ring part, saidupper ring part and said lower ring part being connected together by alower ring bearing, said upper ring part and said lower ring part beingrotatable relative to each other, and a lower rotational drive systemfor driving said upper ring part and said lower ring part in counterrotation about said lower ring bearing; and wherein said tensioningballoons attachment frame has connected thereto an upper ring having anaxis of rotation, a lower ring coaxial with said upper ring, said upperring and said lower ring being connected together by an upper rotaryring bearing, and an upper rotational drive system for driving saidupper ring and said lower ring in counter rotation about said upperrotary ring bearing; said upper rotational drive system and said lowerdrive system being operatively connected to each other to coordinate therotation of said upper ring part and said lower ring to rotate as a unitto keep said associated cables from twisting around each other, saidlower ring part and said upper ring rotating as a unit to counterwind-induced rotation and rotation resulting from the rotation of saidcarriage when the lower end of said one of said respective carriages isheld in said upper ring part and said respective carriage is beingrotated for launch.
 90. A rocket launch system according to claim 89wherein said upper rotational drive system includes: upper forcethrusters for rotating or assisting in the rotation of said upperrotational drive structure; and wherein said lower rotational drivesystem includes lower force thrusters for rotating or assisting therotation of said lower rotational drive system.
 91. A rocket launchsystem according to claim 89 wherein: each said carriage has alongitudinal axis and external radial recesses extending along each saidcarriage, said upper ring part and said lower ring part of said dockingstation are coaxially aligned to define an interior space for receivingand passing therethrough each said carriage; said docking station havinginternal carriage guides for carrying electrical power to said tractiondrives and for entering said radial recesses to keep each said carriagein proper alignment and stable while supplying electrical power to eachsaid carriage.
 92. A rocket launch device according to claim 91 whereineach said carriage has a triangular cross section with corner edges withsaid radial corner recesses extending along said corner edges; said liftring assembly being supported by said tertiary cables, said lift ringassembly comprising: a tubular lift ring with a triangular cross sectionfor receiving each said carriage, said tubular ring comprising: inwardlyextending internal carriage guides engageable with said radial recessesof each said carriage for maintaining the orientation of each saidcarriage in said tubular ring, said tubular ring having a longitudinalaxis coincident with the longitudinal axis of each said carriage, theangle of said longitudinal axis relative to ground is the elevationangle of said tubular ring.
 93. A rocket launch system according toclaim 92 wherein said carriage pivoting assembly tilts said tubular liftring with respect to said secondary cables.
 94. A rocket launch systemaccording to claim 93 wherein a pair of said tertiary cables is onopposite sides of said tubular lift ring, and wherein said carriagepivoting assembly comprises: a rotational drive system operativelyconnected to said tubular lift ring for rotating said tubular ring; liftring guides operatively connected to said tertiary cables; and pivotpins connected to and extending from said tubular lift ring, said pivotpins being pivotally attached to each of said lift ring guides; whereinsaid rotational drive system rotates said tubular lift ring to pivotabout said pivot pins to change the elevation angle of said tubular liftring and each said carriage received thereby.
 95. A rocket launch systemaccording to claim 94 wherein the center of gravity of said tubular liftring falls in the geometric center of said tubular lift ring, saidcenter of gravity being coincident with the axis of said pivot pins. 96.A rocket launch system according to claim 95 wherein said tubular liftring includes a clamping mechanism for releasably locating each saidcarriage with the center of gravity of each said carriage being disposedon the axis of said pivot pins.
 97. A rocket launch system according toclaim 96 wherein said tertiary cables comprise two groups of cables offixed length, said tertiary cables being connected to said lift ringguides to attach said lower hoist assembly to said lift ring guides,said tertiary cables being 180° apart around the circumference of saidlift ring where said tertiary cables are attached to said lower hoistassembly.
 98. A rocket launch system according to claim 96 wherein saidcarriage end gripper includes a set of four orifices sized and arrangedto allow said secondary cables extending between said docking stationand said rotational drive system to freely pass therethrough.
 99. Arocket launch system according to claim 98 wherein said carriage endgripper further include a pair of orifices for allowing said tertiarycables extending between said lift ring assembly and said lower hoistassembly to pass.
 100. A rocket launch system according to claim 99wherein said lighter-than-air balloons provide tension to said threepower and transporting primary cables to enable said primary cables tofunction with a rocket-transporting device disposed on said respectivelines.
 101. A rocket launch system according to claim 100 and furthercomprising: at least one large harness having interconnected arms andtensioning balloon holders on said at least one large harness forattachment to said lighter-than-air balloons, said tensioning balloonholders being attached to said power and transporting primary cables toprovide said tension.
 102. A rocket launch system according to claim 101and further incorporating at least one lower spacer assembly forseparating said three power and transporting primary cables from eachother and attaching said respective tensioning balloon holders to saidrespective large harnesses and to said respective balloons.
 103. Arocket launch system according to claim 102 wherein said at least onelarge harness comprises: three arms forming an equilateral triangle;said at least one lower spacer assembly comprises: three-sided lowerspacer arms forming an equilateral triangle parallel to the respectivearms of said respective large harnesses; said at least one lower spacerassembly having lower spacer assembly-connecting structure at thejuncture of respective lower spacer arms; and said rocket launch systemfurther comprises: lower spacer harness leads connecting said respectivelower spacer assembly-connecting structure with said respectivetensioning balloon holders.
 104. A rocket launch system according toclaim 103 and further incorporating: an upper spacer assembly havingthree arms forming an equilateral triangle having structure at therespective intersections of said three arms for separating said powerand transporting primary cables from each other.
 105. A rocket launchsystem according to claim 104 and further including: upper spacerassembly cable ties connecting the opposite ends of said respectivethree arms to said three arms of said respective large harnesses; andtension ties interconnecting said respective intersections of said threearms of said upper spacer assembly to the respective intersections ofsaid three arms of said respective large harnesses.
 106. A rocket launchassembly according to claim 105 wherein said three arms of said upperspacer assembly are parallel with the respective arms of said respectivelarge harnesses; and wherein said rocket launch system furthercomprises: an upper spacer connecting structure disposed at theintersection of the respective upper spacer arms; and upper spacerconnecting ties interconnecting said respective upper spacer connectingstructure and said opposite ends of said arms of said respective largeharnesses.
 107. A rocket launch system according to claim 106 whereinsaid three arms of said large harness further include: tie holders atthe midpoints of said respective three arms; and said rocket launchsystem further includes: cable leads interconnecting said upper spacerconnecting structure of said arms of said upper spacer assembly and saidtie holders of said respective arms of said at least one large harness.108. A rocket launch system according to claim 107 wherein there are twoor more large harnesses installed periodically along the length of saidset of primary cables with said lighter-than-air balloons attachedthereto to compensate for the full weight of said primary cables.
 109. Arocket launch system according to claim 107 and further including afurther upper spacer assembly for separating said power and transportingprimary cables from each other.
 110. A rocket launch system according toclaim 109 and further including further upper assembly cable tiesconnected to said further upper spacer assembly and said upper harness.111. A rocket launch system according to claim 110 wherein said furtherupper spacer assembly is located above said respective lower spacerassembly, said upper spacer assembly both separating said power andtransporting primary cables from each other and attaching saidrespective tensioning balloon holders to said respective large harnessesand to said respective balloons, where said further upper spacerassembly comprises: three further upper spacer arms forming anequilateral triangle with arms parallel to the respective arms of saidrespective large harnesses; upper spacer arms connecting structuredisposed at the intersection of the respective further upper spacerarms; and a set of further upper spacer connecting ties interconnectssaid respective further upper spacer connecting structure and saidopposite ends of said arms of said respective large harnesses.
 112. Arocket launch system according to claim 111 and further includingstabilizing straps attached to said respective lower spacer assembly andto said upper spacer assembly to prevent said respective primary cablesfrom touching said respective lighter-than-air balloons.
 113. A rocketlaunch system according to claim 112 and further including: a stabilizerconnected intermittently to each of said primary cables between saidprimary cables and said respective lighter-than-air balloons, saidrespective stabilizers including respective connecting members forconnecting said respective stabilizers to said respective stabilizingstraps.
 114. A rocket launch system according to claim 113 wherein eachof said respective stabilizers is composed of three stabilizing armswhich collectively intersect to form an equilateral triangle.
 115. Arocket launch system according to claim 114 wherein a pair ofstabilizing straps is attached to said respective connecting members,said respective pairs of stabilizing straps form various angles; andwherein said rocket launch system includes strap connectors attached tosaid lighter-than-air balloons for enabling said stabilizing straps tocontact said respective lighter-than-air balloons longitudinally.
 116. Arocket launch system according to claim 101 and further including largeharness reaction thrusters operatively connected to said at least onelarge harness for orienting said docking station, said lift ringassembly and said carriage end gripper to be oriented with respect tovertical to compensate for wind forces and for the deflation of any ofsaid lighter-than-air balloons.
 117. A rocket launch system according toclaim 116 and further including position sensors for controlling thedirection and force of said large harness reaction thruster.
 118. Arocket launch system according to claim 117 wherein one of said reactionthrusters is disposed at the intersection of each of the respective armsof said at least one large harness.
 119. A rocket launch systemaccording to claim 118 wherein each of said reaction thrusterscomprises: a fan mounted within a fan housing.
 120. A rocket launchsystem according to claim 119 and wherein said rocket launch systemfurther includes: a pair of arms disposed at the intersection of saidrespective arms of said at least one large harness; and coaxial pinshaving a coaxial axis extending into said respective fan housings forenabling said respective fan housings to pivot about each of saidrespective coaxial axes in clockwise and counterclockwise directions.121. A rocket launch system according to claim 120 wherein said rocketlaunch system further includes: respective rotatable support jointsmounted at said respective tensioning balloon holders; and saidrespective reaction thrusters are pivotably and rotatably gimbaledelectric thrusters for orienting said docking station, said lift ringassembly and said carriage end gripper with respect to vertical tocompensate for wind forces and for deflation of any of saidlighter-than-air balloons.
 122. A rocket launch system according toclaim 99 and further comprising: support cables other than said primarycables for attaching and supporting other items to said primary cables;and support structure for attaching said support cables to saidrespective primary cables, said support structure comprising: at leastone primary cable flange extending from said respective primary cablesin a plane including the longitudinal axis of each of said respectiveprimary cables; a cable support member having cable connecting structurefor connecting an end of said respective cables to said cable supportmember; and at least one cable support member flange attached to saidcable support member for being attached to said at least one primarycable flange.
 123. A rocket launch system according to claim 122 whereinat least one of said at least one primary cable flange and said at leastone cable support member flange is a pair of spaced apart parallelflanges for receiving the other of said at least one primary cableflange and said at least one cable support member flange, and whereinsaid rocket launch system further comprises connecting structure forattaching said at least one primary cable flange and said at least onecable support member flange together.
 124. A rocket launch systemaccording to claim 123 wherein at least one end of said support cablescomprises: a coupling yoke with a pair of spaced apart receiving membershaving aligned lug-receiving holes; wherein said support membercomprises: a support plate having individual lug-receiving holes, saidsupport plate slipping between said spaced apart lug-receiving memberswith said individual lug-receiving hole in alignment with said alignedlug-receiving holes; and a lug fastening said yoke and the cableattached thereto, to said support member.
 125. A rocket launch systemaccording to claim 77 and further comprising: a lower hoist assemblylocated above said lift ring assembly when said rocket launch system isin operation; a set of tertiary cables extending from said lower hoistassembly for being operationally connectable to and supporting said liftring assembly; and a carriage end gripper disposed between said lowerhoist assembly and said lift ring assembly and being operativelyattached to said lower hoist assembly, said carriage end gripper beingreleasably and lockably engageable with a carriage in said lift ringassembly, said lower hoist assembly lifting said end gripper for liftinga carriage into engagement with said carriage pivoting assembly prior tothe launching of a rocket from a carriage disposed in said lift ringassembly.
 126. A rocket launch system according to claim 77 wherein eachsaid carriage includes both retractable arms for holding a rocket andlocking pin receptacles, and wherein said rocket launch system furtherincludes: an upper hoist for lifting each said carriage, said upperhoist comprising: an upper hoist cable, wherein said upper hoist isreelable to either lower or raise said upper hoist cable with respect tosaid upper hoist; a tensioning balloon attachment frame for beingoperatively attached to said tensioning lighter-than-air balloons forboth offsetting the self weight of the cables and supporting saiddocking station and the operational weight of a carriage in said dockingstation with a flight ready rocket in each said carriage, and saidtensioning balloon attachment frame contributing to the tensioning ofthe cables, said tensioning balloon attachment frame comprising: anupper ring and a lower ring, said upper ring and said lower ring beingcounter rotational; a first geared rotational drive system includingfirst reaction force thrusters; a second geared rotational drive systemincluding second reaction force thrusters; wherein said docking stationfurther comprises an upper ring part, a lower ring part and a ringbearing, said first rotational drive system rotating said upper ringpart with respect to said lower ring part; wherein said carriagepivoting assembly comprises a rotational drive system for changing anelevation angle of said tubular lift ring; said first geared rotationaldrive system and said second geared rotational drive system cooperatingto provide opposed rotation of said upper ring with respect to saidlower ring of said tensioning balloon attachment frame, and said firstgeared rotational drive system and said second geared rotational drivesystem cooperating to effect the rotation of said upper ring part ofsaid docking station with said lower ring of said tensioning balloonattachment frame to prevent said cables from twisting around each other;at least two upper force thrusters attached to said tensioning balloonattachment frame and at least two lower force thrusters attached to saiddocking station for countering wind induced rotation and/or rotationresulting from the rotation of a carriage when each said carriage isheld in said upper ring part of said docking station; wherein saidcarriage end gripper grips the upper end of a carriage held by said liftring assembly, and said upper hoist lifts each said carriage end gripperand the carriage out of engagement with said lower ring part of saiddocking station and leaving the lower end of the carriage engaged bysaid upper ring part of said docking station, prior to the launch of arocket from each said carriage; said first geared rotational drivesystem and said second rotational geared drive system rotating saidupper part of said docking station and said lower ring of said tensionballoon attachment frame and parts connected thereto into a desireddirection of azimuth, while said at least two upper force thrusters andsaid at least two lower force thrusters hold said docking station andsaid tension balloon attachment frame steady until a selected optimaldirection in azimuth is reached, whereafter said upper hoist lifts eachof said lower hoist carrier, said carriage end gripper, said tubularlift ring along with a carriage loaded with a rocket to an increasingheight for the safe launch of the rocket in the carriage, and said upperhoist releasing said lock pins from said lock pin receptacles in eachsaid carriage, and said rotational drive system rotates the saidcarriage in said lift ring assembly to a desired elevation angle, andsaid upper hoist raises said carriage end gripper and said carriage endgripper is guided by said secondary cables and said tertiary cables; andsaid upper hoist reels out said upper hoist cable with the assistance ofsaid traction drives to effect the downward travel of carriage theloaded with a rocket at the local acceleration due to gravity, theretractable arms in the carriage being withdrawable from the rocket andthe rocket is boosted clear of the carriage to prevent the rocket fromdamaging any components of said rocket launch system when the rocketengines are fired to launch the rocket into space; the empty carriageand other components suspended by said hoist cable being decelerated bysaid upper hoist and said traction drives, and the carriage beingreinserted into said docking station and returned to earth.
 127. Arocket launch system according to claim 73 wherein said lighter-than-airballoons are operatively attached to said three power and transportingprimary cables intermittently along the length of said three power andtransporting primary cables to support cumulatively said three power andtransporting primary cables, and any other structure carried by saidthree power and transporting primary cables which is utilized in thelaunch of a rocket.
 128. A rocket launch system according to claim 127and further including: respective sets of spacer assemblies locatedintermittently along said three power and transporting primary cables,each of said sets of spacer assemblies having cable engaging structurefor engaging respective ones of said three power and transportingprimary cables to maintain a spaced separation between said respectivethree primary cables, and wherein said lighter-than-air balloons arerespectively, operatively connected to at least one of said spacerassemblies.
 129. A rocket launch system according to claim 73 whereinsaid lighter-than-air balloons are operatively attached to said threepower and transporting primary cables intermittently along the length ofsaid three power and transporting primary cables to support cumulativelysaid three power and transporting primary cables, and any otherstructure carried by said three power and transporting primary cableswhich are utilized in the launch of a rocket.
 130. A rocket launchsystem according to claim 73 wherein each said carriage includes acontinuous heat-and-pressure resistant tube for holding a rocket, saidtube preventing dangerous exhaust gases from leaving each said carriagethrough any side of each said carriage.
 131. A rocket launch systemaccording to claim 72 wherein said carriage comprises: opposed endopenings; and end covers at said respective end openings to protect theinterior of said respective carriage and any rocket contained in saidrespective carriage from the weather.
 132. A rocket launch systemaccording to claim 131 wherein said end covers are retractablemembranes.
 133. A rocket launch system according to claim 131 wherein atleast one of said end covers is movable between open and closedpositions to open and close said at least one end opening.
 134. A rocketlaunch system according to claim 72 wherein said respective carriageshave receptacles for being used to lift said respective carriages intocomponents of said rocket launch system.
 135. A rocket launch systemaccording to claim 134 wherein said receptacles are pin lockreceptacles.
 136. A rocket launch system according to claim 72 whereinsaid carriage comprises: internal retractable arms having an activecondition for holding a rocket securely within said carriage, and beingretracted to an inactive condition to enable launch of the rocket fromsaid carriage.
 137. A rocket launch system according to claim 136wherein said retractable arms hold a rocket with the center of gravityof the rocket being coincident with the center of gravity of saidcarriage.
 138. A rocket launch system according to claim 136 whereinsaid retractable arms comprise: head members; said retractable armshaving an active position wherein said respective head members can enterslots in any rockets having slots for receiving said head members tohold the rocket securely in each said carriage, and an inactive positionwherein said head members are retractable from the respective slots insuch rocket having slots to enable launch of the rocket.
 139. A rocketlaunch system according to claim 138 wherein each said carriagecomprises: a heat-and-pressure resistant tube having a cavity forholding said retractable arms; and protecting doors movable between anopen position enabling movement of said retractable arms to hold arocket, and a closed position to protect said retractable arms.
 140. Arocket launch system according to claim 139 wherein saidheat-and-pressure resistant tube comprises: a cavity-covering end door;an airflow deflector for pivoting between an open position for assistingin enabling said retractable arms to hold a rocket, and a closedposition for assisting in protecting said protecting doors and saidcavity.
 141. A rocket launch system according to claim 140 wherein saidcavity includes: pivot pins for mounting said end door for pivotingbetween said open and closed positions.
 142. A rocket launch systemaccording to claim 140 wherein each of said retractable arms comprises:a base member mounted in said cavity for moving said retractable armbetween said active and said inactive positions; a stem connecting saidbase member to said head member; said retractable arm being movablycoupled to said cavity-covering end door; and wherein said rocket launchsystem further comprises: a hydraulic cylinder movably coupled to saidretractable arm for moving said retractable arm between the active andinactive position of said retractable arm; said hydraulic cylindermoving said retractable arm to the inactive position in response tomovement of said end door to the open position to enable launch of arocket in each said carriage, and moving said retractable arm to theactive position in response to movement of said end door to the closedposition to hold the rockets securely in said respective carriage. 143.A rocket launch system according to claim 72 wherein said carriagecomprises: three sides defining in cross section a triangle, each sideintersecting two other sides to form three intersections; and externalrecesses at said intersections for being guided in respective componentsof said rocket launch system.
 144. A rocket launch system according toclaim 72 wherein said traction drives comprise: a set of traction wheelsassociated with the respective carriages for engaging said at least onepower and transporting primary cable for transporting each said carriagealong said at least one power and transporting primary cable, said setof traction wheels respectively comprising: opposing cylindrical wheelshaving annular grooves for partially enveloping said at least oneprimary cable on which said carriage rides; wherein said traction drivesare a reversible electrically powered energizing apparatus, saidtraction drives derive electrical power from said set of electricalpower lines when said set of traction drives lift each said carriagealong said at least one primary cable, and said reversible electricallypowered energizing apparatus reversibly delivers electrical power tosaid at least one electrical power line when said traction drives movesaid carriage under the influence of gravity to descend said at leastone primary cable.
 145. A rocket launch system according to claim 144wherein said reversible traction drives comprise: a motor generatoroperatively coupled with said respective cylindrical wheels fortransferring electrical power across said rotating cylindrical wheels tosaid at least one primary cable as each said carriage descends said atleast one primary cable.
 146. A rocket launch system according to claim72 wherein each said carriage comprises: a retractable arm for enteringan arm-receiving opening in a respective rocket for holding therespective rocket in said carriage prior to launch, said retractable armbeing retractable from the opening in preparation for launch of therespective rocket.
 147. A rocket launch system according to claim 72wherein each said carriage comprises: an opening for receiving aretractable arm from a respective rocket for holding the respectiverocket in each said carriage prior to launch, said opening enablingretraction of the retractable arm in preparation for launch of therespective rocket.
 148. A rocket launch system according to claim 72 andfurther comprising: a one-occupant rocket to be launched from each saidcarriage, said one-occupant rocket having a steerable motor.
 149. Arocket launch system according to claim 72, and further comprising: amain rocket being launched from each said carriage for being manned byan occupant; and a launch or re-entry space suit worn by the occupant,said space suit comprising: a rigid outer shell with an internal sleeve,said internal sleeve being made of a soft material; a helmet with arigid outer shell; an internal face mask; said space suit being capableof holding a liquid for accommodating G-force effects; an inner suit forlaving close to the occupant wearing said space suit to separate theoccupant from the liquid; an electro-mechanical piston apparatus: acylinder for operatively holding said piston apparatus; said pistonbeing movable in and out of said cylinder, and said piston apparatusbeing operated by electro-mechanical apparatus for controlling thevolume of said suit, for normal respiration; a set of powered jointsprovided at locations corresponding to at least some of the joints ofthe occupant wearing said suit, said powered joints being lockable in anoptimally aerodynamic position for launch, the occupant being uprightand loaded feet first onto the top of said rocket, while resisting theG-force effects of the rocket during launch; and elastic tendons, eachtendon being attached to said suit and being tangent, to said sleeve andbeing attached to said sleeve.
 150. A rocket launch system according toclaim 149, wherein the space suit further includes: a ventilatingapparatus for connecting with an air supply.
 151. A rocket launch systemaccording to claim 149 wherein there is a double seal between the faceof the occupant and said face mask, and wherein said space suit furtherincludes: a leakage tube for draining fluid from said double seal ofsaid face mask.
 152. A rocket launch system according to claim 149wherein said soft material is selected from the group consisting ofelastic webbing, soft open-pore foam and soft open-pore webbing.
 153. Arocket launch system according to claim 72 and further comprising a mainrocket being launched from each said carriage for being manned by anoccupant, and a launch or re-entry suit to be worn by the occupant, saidsuit comprising porous pads on the exterior of said suit for beingfilled with fluid and being substantially fillable with fluid duringlaunch and during re-entry to cool by evaporation the exterior of saidsuit.
 154. A rocket launch system according to claim 72 and furthercomprising a main rocket being launched from each said carriage forbeing manned by an occupant, and a launch or re-entry suit to be worn bythe occupant, said suit comprising an ablative exterior material withthermal insulation.
 155. A rocket launch system according to claim 72and further comprising a main rocket being launched from each saidcarriage for being manned by an occupant, and a launch or re-entry suitto be worn by the occupant, said suit comprising an exterior materialhaving heat-resistant thermal insulation.
 156. A rocket launch systemaccording to claim 72 and further comprising a main rocket for beingcontrollably launchable from each said carriage by said rocket launchsystem, said controlled launch of said main rocket ceasing at a periodafter said controlled launch, a core rocket being releasable from saidmain rocket after launch of said main rocket, and at least one pod forrespectively holding an occupant and being detachably connected to saidcore rocket, said at least one pod being ejectable from said core rocketfor being guided to the earth or a destination in orbit.
 157. A rocketlaunch system according to claim 156 and further comprising a windshieldconnected to said at least one pod for protecting the occupant held insaid at least one pod against high velocity air.
 158. A rocket launchsystem according to claim 72 and further including: a main rocket forbeing launched from each said carriage; at least one pod for beingejectable from said main rocket; and a sled-like re-entry frame includedin said at least one pod, said re-entry frame comprising steering finsand an aerodynamic spike with a disc serving as a forward shockwaveinitiator.
 159. A rocket launch system according to claim 72 and furtherincluding: a rocket for launching from each said carriage; and anaerospace plane attached to the body of said rocket, said aerospaceplane having folded lift and directional control structures attached tothe body of said aerospace plane, and said aerospace plane having wingsmovable between folded and unfolded positions under the control of saidfolded lift and directional control structures.
 160. A rocket launchsystem according to claim 72 and further including a rocket forlaunching from each said carriage; and a lifting-type re-entry vehicle,said lifting-type re-entry vehicle having folded lift and directionalcontrol structures having folded and unfolded configurations.
 161. Arocket launch system according to claim 72 and further including: arocket for launching from each said carriage, said rocket having apayload protected by aerodynamic shells, said aerodynamic shells beingdetachable after said rocket has left the earth's atmosphere followingthe launch of said rocket and said payload has entered space.
 162. Arocket launch system according to claim 72 wherein in the event eachsaid carriage transports a rocket having at least one fin, each saidcarriage comprises: an internal support for holding the rocket, saidinternal support including: slots for receiving the rocket having atleast one fin and holding the rocket having at least one fin stable ineach said carriage.
 163. A rocket launch system according to claim 70wherein said traction drives are reversible traction drives for derivingelectrical power from said at least one electrical power line when saidtraction drives lift said rocket-transporting device along said at leastone rocket-transporting device line, and said reversible traction drivesreversibly deliver electrical power to said at least one electricalpower line when said traction drives move said rocket-transportingdevice under the influence of gravity to descend said at least onerocket-transporting device line.
 164. A rocket launch system accordingto claim 163 wherein said traction drives comprise: a set of tractiondrive wheels associated with said respective carriages for engaging saidat least one electrical power line, and said set of traction drivewheels being operatively connected to said reversible traction drives;said traction drives serving as regenerative brakes when said respectivecarriages move along said at least one rocket-transporting device lineunder the influence of gravity to effect the delivery of electricalpower to said at least one electrical power line during the braking ofsaid respective carriages.
 165. A rocket launch system according toclaim 1 wherein said lighter-than-air balloons are operatively attachedto said at least one electric power line and to at least one saidrocket-transporting device line intermittently along the length of saidat least one power line and said at least one rocket-transporting deviceline to support cumulatively said respective lines, and any otherstructure carried by said at least one transporting device line which isutilized in the launch of a rocket.
 166. A rocket launch systemaccording to claim 1 wherein the electric power is continuouslywithdrawable along said at least one electric power line.
 167. A rocketlaunch system according to claim 166 wherein said at least one electricpower line and said at least one rocket-transporting device line areintegrally combined into at least one power and transporting primarycable.
 168. A rocket launch system according to claim 167 and furthercomprising at least one rocket-transporting device for transporting arocket along said at least one power and transporting primary cable,said at least one rocket-transporting device including: traction drivesfor driving said respective rocket-transporting devices along said atleast one power and transporting primary cable; and a motor-generatorfor deriving electrical power from said at least one electric power lineof said at least one power and transporting primary cable when saidtraction drives require energy to cause said at least onerocket-transporting device to travel upwards on said at least one powerand transporting primary cable, and for supplying electrical power tosaid at least one electric power line when said traction drives generateelectric power when said traction drives retard the downward motion ofsaid at least one rocket-transporting device as said at least onerocket-transporting device travels downwards on said at least one powerand transporting primary cable under the influence of gravity.
 169. Arocket launch system according to claim 168 wherein said respectivetraction drives comprise: a set of traction drive wheels associated witheach of said respective rocket-transporting devices for engaging said atleast one power and transporting primary cables for transporting saidrespective rocket-transporting devices along said at least one power andtransporting primary cable.
 170. A rocket launch system according toclaim 168 wherein said traction drives are reversible traction drivesfor deriving electrical power from said at least one electrical powerline of said at least one power and transporting primary cable when saidtraction drives lift said rocket-transporting device along said at leastone rocket-transporting primary cable, and said reversible tractiondrives reversibly delivers electrical power to said at least oneelectrical power line of said at least one power and transportingprimary cable when said traction drives move said rocket-transportingdevice under the influence of gravity to descend said at least one powerand transporting cable.
 171. A rocket launch system according to claim170 wherein said traction drives comprise: a set of traction drivewheels associated with said respective rocket-transporting devices forengaging said at least one power and transporting primary cable for bothtransporting said rocket-transporting device along said at least onepower and transporting primary cable, and said set of traction drivewheels being operatively connected to said reversible electricallypowered energizing apparatus; said traction drives serving asregenerative brakes when said respective carriages move along said atleast one primary cable under the influence of gravity to effect thedelivery of electrical power to said at least one electric power line ofsaid at least one power and transporting primary cable during thebraking of said respective carriages.
 172. A rocket launch systemaccording to claim 168 wherein said at least one power and transportingprimary cable comprises three power and transporting primary cables forcarrying three-phase power, wherein each of said three power andtransporting primary cables carry one of the phases.
 173. A method forremoving debris from an orbit of the debris around the earth using arocket launch system, the rocket launch system comprising: at least oneelectric power line for carrying electrical power from a source ofelectrical power, at least one power line having a low end portion forbeing positioned at a low altitude and a high end portion for extendinginto high altitudes; at least one rocket-transporting device line fortransporting a rocket-transporting device between a low altitude and ahigh altitude, the at least one rocket-transporting device line having alow end portion for being positioned at a low altitude and a high endportion for extending into high altitudes; wherein the at least onepower line of the at least one electric power line and the at least onerocket-transporting device line lines of the set of rocket-transportingdevice lines are integrally combined into at least one power andtransporting primary cable; lighter-than-air balloons connected to saidat least one power lines and at least one rocket-transporting deviceline for holding said at least one power line and the at least onerocket-transporting device line upwards to a high altitude; a dockingstation operatively connected to the at least one power and transportingprimary cable at a terminal position along the length of said at leastone power and transporting primary cable, the docking station beingstructured to receive a rocket-transporting device as part of apreparation for a launch of a rocket being transported in arocket-transporting device; at least one power and guiding secondarycable operatively attached to the docking station and being extendableto a higher altitude than the altitude of the docking station, therocket launch system further comprising lighter-than-air balloonsoperatively connected to the at least one power and guiding secondarycable for holding and tensioning the at least one power and guidingsecondary cable aloft above the at least one power and transportingprimary cable; and a lift ring assembly in operative engagement with theat least one power and guiding secondary cable for deriving electricalpower from and being guided by the at least one power and guidingsecondary cable, the lift ring assembly being positionable above thedocking station and being operatively engageable with arocket-transporting device disposed in the docking station for liftingthe rocket-transporting device out of the docking station and having arocket-transporting device pivoting assembly for being tilted to adesired rocket launch angle, said lift ring assembly including: atubular ring for maintaining the orientation of a rocket-transportingdevice in the lift ring assembly and being pivotable by the lift ringassembly; and a rotational drive assembly for changing the elevationangle of said tubular ring and a rocket-transporting device heldthereby; a lower hoist assembly located above the lift ring assemblywhen the rocket launch system is in operation; at least one supportingtertiary cable extending from the lower hoist assembly for beingoperationally connectable to and supporting the lift ring assembly; anda rocket-transporting device end gripper disposable between the lowerhoist assembly and the lift ring assembly and being operatively attachedto the lower hoist assembly, the rocket-transporting device end gripperbeing releasably and lockably engageable with a rocket-transportingdevice in the lift ring assembly, the lower hoist assembly lifting therocket-transporting device end gripper for lifting a rocket-transportingdevice into engagement with the rocket-transporting device pivotingassembly prior to the launching of a rocket from a rocket-transportingdevice disposed in said the ring assembly; a rocket-transporting devicefor transporting a rocket along both said at least one power andtransporting cable and the at least one power and guiding secondarycable, the rocket-transporting device including: traction drives fordriving the rocket-transporting device along the at least one power andtransporting primary cable, the traction drives including: anelectrically powered energizing apparatus for deriving electrical powerfrom the at least one power and transporting primary cable when thetraction drives require energy to cause the rocket-transporting deviceto travel upwards on the at least one power and transporting cable;wherein said method comprises: placing a rocket in saidrocket-transporting device; driving the rocket-transporting device witha rocket placed in rocket-transporting device and along the at least onepower and transporting primary cable to the docking station and alongthe at least one power and guiding secondary cable to the lift ringassembly using the traction drives to derive electrical power from boththe respective at least one power and transporting primary cable and theat least one power and guiding secondary cable; using the lower hoistassembly to lower the lift ring assembly to engage the upper part of thedocking station; lowering the end gripper and attaching the end gripperto the rocket-transporting device; using the lower hoist assembly tolift the rocket-transporting device into further engagement with thelift ring assembly such that the combined centers of gravity of the liftring assembly, the rocket-transporting device and the rocket coincidewith the pivot axis of the lift ring assembly; disengaging the endgripper from the rocket-transporting device; guiding the lift ringassembly with the secondary cables and supporting the lift ring assemblywith the tertiary cables, and lifting the rocket-transporting deviceuntil the rocket-transporting device is out of engagement with thedocking station; rotating the tubular ring to put therocket-transporting device at an appropriate angle for launch; actuatingthe rocket to launch the rocket to the orbit of the debris; and usingthe rocket to remove the debris from the orbit.
 174. A rocket launchsystem comprising: at least one electric power line for carryingelectrical power from a source of electrical power from a remoteelectric power system on the earth, the electric power beingcontinuously withdrawable along said at least one electric power line,said at least one electric power line having a low end portion for beingpositioned at a low altitude and a high end portion for extending intohigh altitudes; at least one rocket-transporting device line fortransporting a rocket-transporting device between a low altitude andhigh altitudes, said at least one rocket-transporting device line havinga low end portion for being positioned at a low altitude and a high endportion for extending into higher altitudes; lighter-than-air balloonsconnected to said at least one electric power line and said at least onerocket-transporting device line for supporting said at least oneelectric power line and said at least one rocket-transporting deviceline upwards to a high altitude; a rocket-transporting device fortransporting a rocket along said at least one rocket-transporting deviceline, said rocket-transporting device including: traction drives fordriving said rocket-transporting device along said at least onerocket-transporting device line, said traction drives comprising: amotor-generator for deriving electrical power from said at least oneelectric power line when said traction drives require energy to causesaid rocket-transporting device to travel upwards on said at least onerocket-transporting device line, and for supplying electrical power tosaid at least one electric power line when said motor-generatorgenerates electric power when said traction drives retard the downwardmotion of said rocket-transporting device as said rocket-transportingdevice travels downwards on said at least one rocket-transporting deviceline under the influence of gravity; said rocket-transporting devicecomprising: an interior compartment configured to contain a rocket, therocket being ejectable from said interior compartment during launch;wherein said respective at least one electric power line and said atleast one rocket-transporting device line are integrally combined intoat least one power and transporting primary cable, said respectiverocket-transporting devices being driven along said at least one powerand transporting primary cable by said traction drives upon energizationby said motor-generator.
 175. A rocket launch system according to claim174 wherein said traction drives comprise: a set of traction wheelsassociated with the respective rocket-transporting device for engagingsaid at least one power and transporting primary cable for transportingthe respective rocket-transporting devices along said at least one powerand transporting primary cable, said set of traction wheels respectivelycomprising: opposing cylindrical wheels having annular grooves forpartially enveloping said at least one primary cable on which saidrespective rocket-transporting device rides.